US3854843A - Composite elongate member having a predetermined effective coefficient of linear expansion - Google Patents

Composite elongate member having a predetermined effective coefficient of linear expansion Download PDF

Info

Publication number
US3854843A
US3854843A US00309790A US30979072A US3854843A US 3854843 A US3854843 A US 3854843A US 00309790 A US00309790 A US 00309790A US 30979072 A US30979072 A US 30979072A US 3854843 A US3854843 A US 3854843A
Authority
US
United States
Prior art keywords
shroud ring
stator shroud
rotor
linear expansion
stator
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US00309790A
Inventor
R Penny
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Application granted granted Critical
Publication of US3854843A publication Critical patent/US3854843A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Definitions

  • stator shroud ring assembly in which a turbine of-a gas turbine engine is positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor,the stator shroud ring assembly including a stator shroud ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the co-efficients of linear expansion of the materials employed and the total arcuate length employed of each material being such that the circumferential length of whole shroud ring will change with temperature by an amount corresponding to a predetermined effective co-efficient of linear expansion substantially equal to that of the rotor material.
  • the invention relates to a composite elongate member having a predetermined effective coefficient of linear expansion and is particularly, but not exclusively, concerned with a stator shroud ring assembly to be arranged concentrically around a turbine rotor of a gas turbine engine.
  • a stator shroud ring is provided around the periphery of a turbine rotor to define the radially outer boundary of the working fluid passage through the turbine.
  • the blades of the rotor may themselves be unshrouded or they may be provided with a shroud integral with the blades and concentric with the stator shroud ring.
  • There must ofcourse be running clearance provided by an annular gap of a predetermined radial thickness between the tips of the blades, where they are unshrouded, and the stator shroud ring or between the rotor shroud ring, where provided, and the stator shroud ring.
  • the turbine rotor including the blades and the rotor shroud ring, where provided, is made of a material selected to withstand the necessary high working temperatures.
  • the stator shroud ring is subjected to the same working temperatures and is likewise made of a material capable of withstanding high temperature.
  • stator shroud ring will expand more than the rotor and therefore the annular gap will increase in radial thickness as working temperature increases. This is because the temperature gradient radially of the rotor increases from the hub to the blade tips or the rotor shroud ring, where provided. The increase in the radial thickness of the gap results in loss of performance when the turbine has reached its operating temperature, because there must be a minimum clearance when the turbine is cold to prevent the rotor rubbing against the stator shroud ring.
  • An object of the invention is to provide a stator shroud ring which'will have substantially the same radial expansion characteristics as the rotor, thereby resulting in an annular gap between the rotor and the stator shroud ring of substantially uniform radial thickness throughout the range'of operating temperature of the turbine.
  • a composite elongate member is constructed from at least one portion madeof one material and at least one portion made .of an-' other material, the portions being assembled end-toend and the co-efficients of linear expansion of the materials employed and the total length employed of each material being such that the whole member when subjected to a temperature change will-change in length by an amount corresponding to a predetermined effective co-efficie'nt of linear expansion,
  • the invention also provides a stator shroud ring assembly in which a turbine rotor of a gas turbine engine is to be positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ring assembly including a stator shroud-ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the arcuate portions being assembled end-to-end and the co-efficients of linear expansion of efficient of linear expansion as the nickel-based alloy;
  • stator shroud ring is formed from arcuate portions of two different materials but arcuate portions made of more than two materials may be used if desired.
  • one of the materials from whichthe arcuate portions are made is the same as that from which the rotor is formed, the other material or materials having a lower co-efficient of expansion, whereby the effective expansion of thecomposite stator shroud ring will be substantially the same as that of the rotor.
  • the arcuate portions. may have interengageable end faces.
  • the arcuate portions may be bounded by a concentric enveloping ring made of a material having a co-v efficient of linear expansion substantially the same as the material from which the turbine rotor is formed.
  • the material of the concentric enveloping ring may have inferior stress rupture properties compared with the material from which the rotor is made.
  • the invention also includes a gas turbine including a rotor and a stator shroud'ring assembly inaccordance with any one of the five immediately preceding paragraphs.
  • FIG. 1 isan axial section through a peripheral portion of the turbine
  • FIG. 2 is an end view of the turbine shown in FIG. 1;
  • FIG. 3 shows a modified form of the stator shroud 'ring shown in FIG. 2, and
  • FIG. 4 is' a view similar to FIG. 1' showing a further modification.
  • the turbine has a stator shroud ring formed from a plurality of arcuate portions l, 2 two or more abutted together circumferentially to 'form a complete annulus;
  • arcuate portions 1 are made of 'two different materials but where there are more than two arcuate portions more than two materials may be used.
  • One or more of the arcuate portions 1 are made of the same material as the rotor 12, e.g.,'
  • arcuate portion or portions 2 are made of a ceramic or ceramic-like material, such as silicon nitride.
  • the arcuate portions are held within an enveloping concentric outer ring 3 which may be made of a material having the same cobut which may be made of a cheaper material having an inferior stress rupture property, which itself would not be capable of withstanding the stresses to which the stator shroud ring will be subjected during operation of the turbine.
  • the ratio of the total circumferential length of the arcuate portions 2t0 the total circumferential length of the alloy portions 1 is such that the effective co-efficient of linear expansion of the composite stator shroud ring is substantially equal to the coefficient of linear expansion of the material of the rotor.
  • the effective relative coefficient of linear expansion of the composite stator ring could also be made to be 12 by making the ratio of the circumferential lengths of the alloy to ceramic segmental portions in the ratio of 3:2.
  • the radial dimension of the gap X between the stator shroud ring and the tips of the rotor blades, or the rotor blade shroud ring, where provided, is maintained substantially constant over the range of operating temperatures for which the turbine has been designed.
  • the composite shroud ring 1, 2 may extend over a ring of nozzle guide vanes as well as the rotor blades.
  • the arcuate portions 1, 2 may have interengaging ends, such as ribs and notches 6 to maintain correct relative location of the portions.
  • each of 7 the portions may be made concave and convex respectively as shown at 7 in FIG. 3. This construction would also maintain adjacent ends of theportions at the correct radial locations.
  • FIG. 4 shows a modification of the construction I shown in FIG. 2 in which the concentric enveloping ring 8 is tapered in the axial direction and is engaged with a frusto-conical face of a housing member 9.
  • a spring 10 acts betwen the ring 8 and a second housing member 1 l and thereby urges the ring 8 by wedging ac-- tion radially inwardly against the composite: ring 1, 2.
  • the arcuate portions 1, 2 will be maintained in end-to-end abutment.
  • stator shroud ring assembly in which a turbine of a gas turbine engine is to be positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ring assembly including a stator shroud ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the arcuate portions being assembled ,end-to-end and the co-efficients of linear expansion of the material employed and the total arcuate length employed of each material'being such that the circumferential length of the whole shroud ring will change with temperature, within the range of working temperature for which the engine has been designed, by an amount corresponding to a predetermined effective cO-efficient of linear expansion, whereby the total change in circumferential length of the stator shroud ring will substantially correspond to the alteration in diameter of the rotor, the radial dimension of said annular gap thereby being maintained at substantially the afores
  • stator shroud ring assembly as claimed in claim 1 in which thestator shroud ring is formed from arcuate portions of two different materials.
  • a stator shroud ring assembly as claimed in claim 1 in which a concentric enveloping ring made of a material having a co-efiicient of linear expansion substantially the same as the material from which the turbine rotor is made bounds the arcuate portions of the stator shroud ring.
  • a gas turbine engine including a bladed turbine rotor and a stator shroud ring assembly, the latter defining a stator shroud ring surrounding the rotor with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ringbeing constructed from at least one arcuate portion made of one material and at least one arcuate portion madeof another material, the arcuate portions being assembled end-to-end andthe co-efficients of linearexpansion of the materials employed and the total arcuate length employed of each material being such that the circumferential responding to a predetermined effective c'o-efficient of linear expansion, whereby the total change in circumferential length of the stator shroud ring will substantially correspond to the alteration in diameter of the rotor, the radial dimension of said annular gap thereby being maintained at substantially the aforesaid predetermined value.

Abstract

A stator shroud ring assembly in which a turbine of a gas turbine engine is positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ring assembly including a stator shroud ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the co-efficients of linear expansion of the materials employed and the total arcuate length employed of each material being such that the circumferential length of whole shroud ring will change with temperature by an amount corresponding to a predetermined effective co-efficient of linear expansion substantially equal to that of the rotor material.

Description

Penny COMPOSITE ELONGATE MEMBER HAVING A PREDETERMINED EFFECTIVE COEFFICIENT OF LINEAR EXPANSION [76] Inventor: Robert Noel Penny, 12 Alderbrook Rd., Solihull, England [22] Filed: Nov. 27, 1972 [21] App]. No.: 309,790
[30] Foreign Application Priority Data Dec. 1, 1971 Great Britain 55665/71 [52] US. Cl 415/197, 415/214, 415/219 R [51] Int. Cl. F04d 19/00, F04d 29/02 [58] Field of Search 418/134, 136; 415/214,
[56] References Cited UNITED STATES PATENTS 2,555,256 5/1951 Tyson 415/214 2,863,634 12/1958 Chamberlin et al.... 415/134 2,962,256 11/1960 Bishop 1 415/136 3,085,398 4/1963 Ingleson 60/3932 3,430,898 3/1969 Parechanian et a1. 415/214 Dec. 17, 1974 FOREIGN PATENTS OR APPLICATIONS 1,247,283 10/1960 France 416/196 Primary ExaminerHenry F. Raduazo Attorney, Agent, or FirmMawhinney & Mawhinney [57 ABSTRACT A stator shroud ring assembly in which a turbine of-a gas turbine engine is positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor,the stator shroud ring assembly including a stator shroud ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the co-efficients of linear expansion of the materials employed and the total arcuate length employed of each material being such that the circumferential length of whole shroud ring will change with temperature by an amount corresponding to a predetermined effective co-efficient of linear expansion substantially equal to that of the rotor material.
6 C1aims, 4 Drawing Figures COMPOSITE ELONGATE MEMBER HAVING A PREDETERMINED EFFECTIVE COEFFICIENT OF LINEAR EXPANSION The invention relates to a composite elongate member having a predetermined effective coefficient of linear expansion and is particularly, but not exclusively, concerned with a stator shroud ring assembly to be arranged concentrically around a turbine rotor of a gas turbine engine.
A A stator shroud ring is provided around the periphery of a turbine rotor to define the radially outer boundary of the working fluid passage through the turbine. The blades of the rotor may themselves be unshrouded or they may be provided with a shroud integral with the blades and concentric with the stator shroud ring. There must ofcourse be running clearance provided by an annular gap of a predetermined radial thickness between the tips of the blades, where they are unshrouded, and the stator shroud ring or between the rotor shroud ring, where provided, and the stator shroud ring.
The turbine rotor, including the blades and the rotor shroud ring, where provided, is made of a material selected to withstand the necessary high working temperatures. Similarly, the stator shroud ring is subjected to the same working temperatures and is likewise made of a material capable of withstanding high temperature.
Where the rotor and the stator shroud ring are made of the same material, it has been found that the stator shroud ring will expand more than the rotor and therefore the annular gap will increase in radial thickness as working temperature increases. This is because the temperature gradient radially of the rotor increases from the hub to the blade tips or the rotor shroud ring, where provided. The increase in the radial thickness of the gap results in loss of performance when the turbine has reached its operating temperature, because there must be a minimum clearance when the turbine is cold to prevent the rotor rubbing against the stator shroud ring. An object of the invention is to provide a stator shroud ring which'will have substantially the same radial expansion characteristics as the rotor, thereby resulting in an annular gap between the rotor and the stator shroud ring of substantially uniform radial thickness throughout the range'of operating temperature of the turbine.
According to the invention, a composite elongate member is constructed from at least one portion madeof one material and at least one portion made .of an-' other material, the portions being assembled end-toend and the co-efficients of linear expansion of the materials employed and the total length employed of each material being such that the whole member when subjected to a temperature change will-change in length by an amount corresponding to a predetermined effective co-efficie'nt of linear expansion,
The invention also provides a stator shroud ring assembly in which a turbine rotor of a gas turbine engine is to be positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ring assembly including a stator shroud-ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the arcuate portions being assembled end-to-end and the co-efficients of linear expansion of efficient of linear expansion as the nickel-based alloy; I
of the rotor, the radial dimension of the annular gap thereby being maintained at substantially the aforesaid predeterminedvalue.
Conveniently the stator shroud ring is formed from arcuate portions of two different materials but arcuate portions made of more than two materials may be used if desired.
Conveniently, one of the materials from whichthe arcuate portions are made is the same as that from which the rotor is formed, the other material or materials having a lower co-efficient of expansion, whereby the effective expansion of thecomposite stator shroud ring will be substantially the same as that of the rotor.
The arcuate portions. may have interengageable end faces.
The arcuate portions may be bounded by a concentric enveloping ring made of a material having a co-v efficient of linear expansion substantially the same as the material from which the turbine rotor is formed. The material of the concentric enveloping ring may have inferior stress rupture properties compared with the material from which the rotor is made.
The invention also includes a gas turbine including a rotor and a stator shroud'ring assembly inaccordance with any one of the five immediately preceding paragraphs. v
By way of example, a gas turbine having a composite stator shroud ring in accordance with the invention is now described with reference to the accompanying V drawings, in which:
FIG. 1 isan axial section through a peripheral portion of the turbine;
FIG. 2 is an end view of the turbine shown in FIG. 1;
FIG. 3 shows a modified form of the stator shroud 'ring shown in FIG. 2, and
FIG. 4 is' a view similar to FIG. 1' showing a further modification.
Referring to FIGS. 1 and 2 the turbine has a stator shroud ring formed from a plurality of arcuate portions l, 2 two or more abutted together circumferentially to 'form a complete annulus; The segmental portions 1, 2
are made of 'two different materials but where there are more than two arcuate portions more than two materials may be used. One or more of the arcuate portions 1 are made of the same material as the rotor 12, e.g.,'
a nickel-based alloy, and the other arcuate portion or portions 2 are made of a ceramic or ceramic-like material, such as silicon nitride. The arcuate portions are held within an enveloping concentric outer ring 3 which may be made of a material having the same cobut which may be made of a cheaper material having an inferior stress rupture property, which itself would not be capable of withstanding the stresses to which the stator shroud ring will be subjected during operation of the turbine. The ratio of the total circumferential length of the arcuate portions 2t0 the total circumferential length of the alloy portions 1 is such that the effective co-efficient of linear expansion of the composite stator shroud ring is substantially equal to the coefficient of linear expansion of the material of the rotor. For example, where the relative co-efficient of linear expansion of the alloy is 18 and the relative coefficient of linear expansion of the ceramic material is 3 and thethermal gradient radially of the turbine rotor results in the effective relative co-efficient of linear expansion of the rotor being 12, the effective relative coefficient of linear expansion of the composite stator ring could also be made to be 12 by making the ratio of the circumferential lengths of the alloy to ceramic segmental portions in the ratio of 3:2.
By making the effective linear co-efficient of expansion of the composite stator shroud ring substantially equal to the co-efficient of linear expansion of the ma terial from which the rotor is made, the radial dimension of the gap X between the stator shroud ring and the tips of the rotor blades, or the rotor blade shroud ring, where provided, is maintained substantially constant over the range of operating temperatures for which the turbine has been designed.
The external concentric envelopingring 3 may be located from movement in the axial direction by clamping it between two housing parts 4 and 5, such as the nozzle guide vane supporting ring'and another annular shroud positioned between the turbine rotor and an adjacent rotor. The ring 3 may make a shrink fit in one or both of the housing parts.
The composite shroud ring 1, 2 may extend over a ring of nozzle guide vanes as well as the rotor blades.
As shown in FlG. 2, the arcuate portions 1, 2 may have interengaging ends, such as ribs and notches 6 to maintain correct relative location of the portions. Al-
ternatively the opposite circumferential ends of each of 7 the portions may be made concave and convex respectively as shown at 7 in FIG. 3. This construction would also maintain adjacent ends of theportions at the correct radial locations.
FIG. 4 shows a modification of the construction I shown in FIG. 2 in which the concentric enveloping ring 8 is tapered in the axial direction and is engaged with a frusto-conical face of a housing member 9. A spring 10 acts betwen the ring 8 and a second housing member 1 l and thereby urges the ring 8 by wedging ac-- tion radially inwardly against the composite: ring 1, 2. Hence the arcuate portions 1, 2 will be maintained in end-to-end abutment.
What I claim as my invention and desire to secure by Letters Patent of the United States is:
1. A stator shroud ring assembly in which a turbine of a gas turbine engine is to be positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ring assembly including a stator shroud ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the arcuate portions being assembled ,end-to-end and the co-efficients of linear expansion of the material employed and the total arcuate length employed of each material'being such that the circumferential length of the whole shroud ring will change with temperature, within the range of working temperature for which the engine has been designed, by an amount corresponding to a predetermined effective cO-efficient of linear expansion, whereby the total change in circumferential length of the stator shroud ring will substantially correspond to the alteration in diameter of the rotor, the radial dimension of said annular gap thereby being maintained at substantially the aforesaid predetemiined value.
2. A stator shroud ring assembly as claimed in claim 1 in which thestator shroud ring is formed from arcuate portions of two different materials.
3. A stator shroud ring assembly as claimed in claim 1 in which one of the materials from which the arcuate portions are made is the same as that from which the rotor is formed, the material of the remaining arcuate portions having a lowerco-efficient of expansion,
whereby the effective expansion of the composite stator shroud ring is substantially the same as that of the rotor.
4'. A stator shroud ring assembly as claimed in claim 1 in which the arcuate portions have interengageable end faces. I
5. A stator shroud ring assembly as claimed in claim 1 in which a concentric enveloping ring made of a material having a co-efiicient of linear expansion substantially the same as the material from which the turbine rotor is made bounds the arcuate portions of the stator shroud ring.
6. A gas turbine engine including a bladed turbine rotor and a stator shroud ring assembly, the latter defining a stator shroud ring surrounding the rotor with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ringbeing constructed from at least one arcuate portion made of one material and at least one arcuate portion madeof another material, the arcuate portions being assembled end-to-end andthe co-efficients of linearexpansion of the materials employed and the total arcuate length employed of each material being such that the circumferential responding to a predetermined effective c'o-efficient of linear expansion, whereby the total change in circumferential length of the stator shroud ring will substantially correspond to the alteration in diameter of the rotor, the radial dimension of said annular gap thereby being maintained at substantially the aforesaid predetermined value.

Claims (6)

1. A stator shroud ring assembly in which a turbine of a gas turbine engine is to be positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ring assembly including a stator shroud ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the arcuate portions being assembled end-to-end and the co-efficients of linear expansion of the material employed and the total arcuate length employed of each material being such that the circumferential length of the whole shroud ring will change with temperature, within the range of working temperature for which the engine has been designed, by an amount corresponding to a predetermined effective co-efficient of linear expansion, whereby the total change in circumferential length of the stator shroud ring will substantially correspond to the alteration in diameter of the rotor, the radial dimension of said annular gap thereby being maintained at substantially the aforesaid predetermined value.
2. A stator shroud ring assembly as claimed in claim 1 in which the stator shroud ring is formed from arcuate portions of two different materials.
3. A stator shroud ring assembly as claimed in claim 1 in which one of the materials from which the arcuate portions are made is the same as that from which the rotor is formed, the material of the remaining arcuate portions having a lower co-efficient of expansion, whereby the effective expansion of the composite stator shroud ring is substantially the same as that of the rotor.
4. A stator shroud ring assembly as claimed in claim 1 in which the arcuate portions have interengageable end faces.
5. A stator shroud ring assembly as claimed in claim 1 in which a concentric enveloping ring made of a material having a co-efficient of linear expansion substantially the same as the material from which the turbine rotor is made bounds the arcuate portions of the stator shroud ring.
6. A gas turbine engine including a bladed turbine rotor and a stator shroud ring assembly, the latter defining a stator shroud ring surrounding the rotor with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ring being constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the arcuate portions being assembled end-to-end and the co-efficients of linear expansion of the materials employed and the total arcuate length employed of each material being such that the circumferential length of the whole shroud ring will change with temperature, within the range of working temperature for which the engine has been designed, by an amount corresponding to a predetermined effective co-efficient of linear expansion, whereby the total change in circumferential length of the stator shroud ring will substantially correspond to the alteration in diameter of the rotor, the radial dimension of said annular gap thereby being maintained at substantially the aforesaid predetermined value.
US00309790A 1971-12-01 1972-11-27 Composite elongate member having a predetermined effective coefficient of linear expansion Expired - Lifetime US3854843A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5566571A GB1363897A (en) 1971-12-01 1971-12-01 Composite elongate member having a predetermined effective coeffi cient of linear expansion

Publications (1)

Publication Number Publication Date
US3854843A true US3854843A (en) 1974-12-17

Family

ID=10474529

Family Applications (1)

Application Number Title Priority Date Filing Date
US00309790A Expired - Lifetime US3854843A (en) 1971-12-01 1972-11-27 Composite elongate member having a predetermined effective coefficient of linear expansion

Country Status (12)

Country Link
US (1) US3854843A (en)
JP (1) JPS5138371B2 (en)
AU (1) AU463454B2 (en)
BE (1) BE792224A (en)
CA (1) CA989312A (en)
CH (1) CH561354A5 (en)
DE (1) DE2258480A1 (en)
FR (1) FR2164215A5 (en)
GB (1) GB1363897A (en)
IT (1) IT975912B (en)
NL (1) NL7216110A (en)
SE (1) SE385941B (en)

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS52143312A (en) * 1976-05-24 1977-11-29 Hitachi Ltd Steam seal ring
US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
US4669954A (en) * 1985-01-24 1987-06-02 Societe Europeenne De Propulsion Abradable turbine rings and turbines thus obtained
US4768924A (en) * 1986-07-22 1988-09-06 Pratt & Whitney Canada Inc. Ceramic stator vane assembly
US5388959A (en) * 1993-08-23 1995-02-14 General Electric Company Seal including a non-metallic abradable material
EP1059420A1 (en) * 1999-06-10 2000-12-13 Snecma Moteurs Housing for a high pressure compressor
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
US20030185674A1 (en) * 2002-03-28 2003-10-02 General Electric Company Shroud segment and assembly for a turbine engine
US20040200642A1 (en) * 2000-06-21 2004-10-14 Downie Andrew Mcpherson Drilling turbine
US20040240519A1 (en) * 2003-04-28 2004-12-02 Steve Ingistov Method for monitoring the performance of a turbine
US20060013683A1 (en) * 2004-07-15 2006-01-19 Rolls-Royce Plc. Spacer arrangement
US20060013681A1 (en) * 2004-05-17 2006-01-19 Cardarella L J Jr Turbine case reinforcement in a gas turbine jet engine
US20060059889A1 (en) * 2004-09-23 2006-03-23 Cardarella Louis J Jr Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
US20070243062A1 (en) * 2006-04-14 2007-10-18 Chevrette Richard J Steam turbine variable clearance packing
US20080131270A1 (en) * 2006-12-04 2008-06-05 Siemens Power Generation, Inc. Blade clearance system for a turbine engine
WO2013110792A1 (en) * 2012-01-26 2013-08-01 Alstom Technology Ltd Stator component with segmented inner ring for a turbomachine
US20150016946A1 (en) * 2013-02-23 2015-01-15 Rolls-Royce North American Technologies, Inc. Blade clearance control for gas turbine engine
US20150097342A1 (en) * 2013-10-09 2015-04-09 Snecma Labyrinth seal and rotating machine comprising such a seal
US20160146042A1 (en) * 2013-06-28 2016-05-26 Siemens Aktiengesellschaft Gas turbine and heat shield for a gas turbine
US9441501B2 (en) 2009-05-05 2016-09-13 General Electric Company Turbine shell with pin support
US11008882B2 (en) * 2019-04-18 2021-05-18 Rolls-Royce North American Technologies Inc. Blade tip clearance assembly
US11802257B2 (en) 2022-01-31 2023-10-31 Marathon Petroleum Company Lp Systems and methods for reducing rendered fats pour point
US11860069B2 (en) 2021-02-25 2024-01-02 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11891581B2 (en) 2017-09-29 2024-02-06 Marathon Petroleum Company Lp Tower bottoms coke catching device
US11898109B2 (en) 2021-02-25 2024-02-13 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of hydrotreating and fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11905468B2 (en) 2021-02-25 2024-02-20 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11905479B2 (en) 2020-02-19 2024-02-20 Marathon Petroleum Company Lp Low sulfur fuel oil blends for stability enhancement and associated methods
US11970664B2 (en) 2023-05-08 2024-04-30 Marathon Petroleum Company Lp Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3986720A (en) * 1975-04-14 1976-10-19 General Electric Company Turbine shroud structure
JPS5242906U (en) * 1975-09-22 1977-03-26
JPS52127105U (en) * 1976-03-25 1977-09-27
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
US4411594A (en) * 1979-06-30 1983-10-25 Rolls-Royce Limited Support member and a component supported thereby
GB2165590B (en) * 1984-10-09 1988-05-05 Rolls Royce Improvements in or relating to rotor tip clearance control devices
FR2572394B1 (en) * 1984-10-30 1986-12-19 Snecma METHOD FOR MANUFACTURING A CERAMIC TURBINE RING INTEGRATED WITH AN ANNULAR METAL SUPPORT
FR2577281B1 (en) * 1985-02-13 1987-03-20 Snecma TURBOMACHINE HOUSING ASSOCIATED WITH A DEVICE FOR ADJUSTING THE GAP BETWEEN MOBILE BLADES AND HOUSING
GB8921003D0 (en) * 1989-09-15 1989-11-01 Rolls Royce Plc Improvements in or relating to shroud rings
CA2039756A1 (en) * 1990-05-31 1991-12-01 Larry Wayne Plemmons Stator having selectively applied thermal conductivity coating
US5332358A (en) * 1993-03-01 1994-07-26 General Electric Company Uncoupled seal support assembly
DE4309199A1 (en) * 1993-03-22 1994-09-29 Abb Management Ag Device for the fixing of heat accumulation segments and stator blades in axial flow turbines
US6896483B2 (en) * 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
DE102013210876B4 (en) * 2013-06-11 2015-02-26 MTU Aero Engines AG Composite component for thermal clearance control in a turbomachine and this turbomachine containing
US10815816B2 (en) * 2018-09-24 2020-10-27 General Electric Company Containment case active clearance control structure

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2555256A (en) * 1948-04-14 1951-05-29 Nat Tube Co Pipe-line pipe
US2863634A (en) * 1954-12-16 1958-12-09 Napier & Son Ltd Shroud ring construction for turbines and compressors
FR1247283A (en) * 1959-02-09 1960-11-25 Westinghouse Electric Corp Turbine apparatus
US2962256A (en) * 1956-03-28 1960-11-29 Napier & Son Ltd Turbine blade shroud rings
US3085398A (en) * 1961-01-10 1963-04-16 Gen Electric Variable-clearance shroud structure for gas turbine engines
US3430898A (en) * 1967-05-01 1969-03-04 Us Navy Leading edge for hypersonic vehicle

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2555256A (en) * 1948-04-14 1951-05-29 Nat Tube Co Pipe-line pipe
US2863634A (en) * 1954-12-16 1958-12-09 Napier & Son Ltd Shroud ring construction for turbines and compressors
US2962256A (en) * 1956-03-28 1960-11-29 Napier & Son Ltd Turbine blade shroud rings
FR1247283A (en) * 1959-02-09 1960-11-25 Westinghouse Electric Corp Turbine apparatus
US3085398A (en) * 1961-01-10 1963-04-16 Gen Electric Variable-clearance shroud structure for gas turbine engines
US3430898A (en) * 1967-05-01 1969-03-04 Us Navy Leading edge for hypersonic vehicle

Cited By (49)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS52143312A (en) * 1976-05-24 1977-11-29 Hitachi Ltd Steam seal ring
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4669954A (en) * 1985-01-24 1987-06-02 Societe Europeenne De Propulsion Abradable turbine rings and turbines thus obtained
US4768924A (en) * 1986-07-22 1988-09-06 Pratt & Whitney Canada Inc. Ceramic stator vane assembly
US5388959A (en) * 1993-08-23 1995-02-14 General Electric Company Seal including a non-metallic abradable material
US6390771B1 (en) 1999-06-10 2002-05-21 Snecma Moteurs High-pressure compressor stator
EP1059420A1 (en) * 1999-06-10 2000-12-13 Snecma Moteurs Housing for a high pressure compressor
FR2794816A1 (en) * 1999-06-10 2000-12-15 Snecma HIGH PRESSURE COMPRESSOR STATOR
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
US20040200642A1 (en) * 2000-06-21 2004-10-14 Downie Andrew Mcpherson Drilling turbine
US7204326B2 (en) * 2000-06-21 2007-04-17 Smith International, Inc. Drilling turbine
US20030185674A1 (en) * 2002-03-28 2003-10-02 General Electric Company Shroud segment and assembly for a turbine engine
US6733235B2 (en) * 2002-03-28 2004-05-11 General Electric Company Shroud segment and assembly for a turbine engine
US20040240519A1 (en) * 2003-04-28 2004-12-02 Steve Ingistov Method for monitoring the performance of a turbine
US7013718B2 (en) * 2003-04-28 2006-03-21 Watson Cogeneration Company Method for monitoring the performance of a turbine
US20060013681A1 (en) * 2004-05-17 2006-01-19 Cardarella L J Jr Turbine case reinforcement in a gas turbine jet engine
US20060013683A1 (en) * 2004-07-15 2006-01-19 Rolls-Royce Plc. Spacer arrangement
US7396203B2 (en) * 2004-07-15 2008-07-08 Rolls-Royce, Plc Spacer arrangement
US8191254B2 (en) 2004-09-23 2012-06-05 Carlton Forge Works Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
US20060059889A1 (en) * 2004-09-23 2006-03-23 Cardarella Louis J Jr Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
US8317456B2 (en) 2004-09-23 2012-11-27 Carlton Forge Works Fan case reinforcement in a gas turbine jet engine
US8454298B2 (en) 2004-09-23 2013-06-04 Carlton Forge Works Fan case reinforcement in a gas turbine jet engine
US20070243062A1 (en) * 2006-04-14 2007-10-18 Chevrette Richard J Steam turbine variable clearance packing
US7484927B2 (en) * 2006-04-14 2009-02-03 General Electric Company Steam turbine variable clearance packing
US7686569B2 (en) * 2006-12-04 2010-03-30 Siemens Energy, Inc. Blade clearance system for a turbine engine
US20080131270A1 (en) * 2006-12-04 2008-06-05 Siemens Power Generation, Inc. Blade clearance system for a turbine engine
US9441501B2 (en) 2009-05-05 2016-09-13 General Electric Company Turbine shell with pin support
WO2013110792A1 (en) * 2012-01-26 2013-08-01 Alstom Technology Ltd Stator component with segmented inner ring for a turbomachine
CN104066934A (en) * 2012-01-26 2014-09-24 阿尔斯通技术有限公司 Stator component with segmented inner ring for a turbomachine
US9702262B2 (en) 2012-01-26 2017-07-11 Ansaldo Energia Ip Uk Limited Stator component with segmented inner ring for a turbomachine
US9587507B2 (en) * 2013-02-23 2017-03-07 Rolls-Royce North American Technologies, Inc. Blade clearance control for gas turbine engine
US20150016946A1 (en) * 2013-02-23 2015-01-15 Rolls-Royce North American Technologies, Inc. Blade clearance control for gas turbine engine
US20160146042A1 (en) * 2013-06-28 2016-05-26 Siemens Aktiengesellschaft Gas turbine and heat shield for a gas turbine
US9551233B2 (en) * 2013-10-09 2017-01-24 Snecma Labyrinth seal and rotating machine comprising such a seal
US20150097342A1 (en) * 2013-10-09 2015-04-09 Snecma Labyrinth seal and rotating machine comprising such a seal
GB2520818B (en) * 2013-10-09 2020-01-29 Snecma Labyrinth seal and rotating machine comprising such a seal
US11891581B2 (en) 2017-09-29 2024-02-06 Marathon Petroleum Company Lp Tower bottoms coke catching device
US11008882B2 (en) * 2019-04-18 2021-05-18 Rolls-Royce North American Technologies Inc. Blade tip clearance assembly
US11920096B2 (en) 2020-02-19 2024-03-05 Marathon Petroleum Company Lp Low sulfur fuel oil blends for paraffinic resid stability and associated methods
US11905479B2 (en) 2020-02-19 2024-02-20 Marathon Petroleum Company Lp Low sulfur fuel oil blends for stability enhancement and associated methods
US11885739B2 (en) 2021-02-25 2024-01-30 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11898109B2 (en) 2021-02-25 2024-02-13 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of hydrotreating and fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11905468B2 (en) 2021-02-25 2024-02-20 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11906423B2 (en) 2021-02-25 2024-02-20 Marathon Petroleum Company Lp Methods, assemblies, and controllers for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11860069B2 (en) 2021-02-25 2024-01-02 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11921035B2 (en) 2021-02-25 2024-03-05 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11802257B2 (en) 2022-01-31 2023-10-31 Marathon Petroleum Company Lp Systems and methods for reducing rendered fats pour point
US11970664B2 (en) 2023-05-08 2024-04-30 Marathon Petroleum Company Lp Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive

Also Published As

Publication number Publication date
SE385941B (en) 1976-07-26
CA989312A (en) 1976-05-18
JPS5138371B2 (en) 1976-10-21
GB1363897A (en) 1974-08-21
JPS4863111A (en) 1973-09-03
AU463454B2 (en) 1975-07-24
BE792224A (en) 1973-03-30
NL7216110A (en) 1973-06-05
IT975912B (en) 1974-08-10
CH561354A5 (en) 1975-04-30
FR2164215A5 (en) 1973-07-27
DE2258480A1 (en) 1973-06-07
AU4931272A (en) 1974-06-06

Similar Documents

Publication Publication Date Title
US3854843A (en) Composite elongate member having a predetermined effective coefficient of linear expansion
US4512712A (en) Turbine stator assembly
US6315519B1 (en) Turbine inner shroud and turbine assembly containing such inner shroud
US3126149A (en) Foamed aluminum honeycomb motor
US4411594A (en) Support member and a component supported thereby
US4759687A (en) Turbine ring incorporating elements of a ceramic composition divided into sectors
US4820119A (en) Inner turbine seal
CA2523192C (en) Turbine shroud segment seal
US2654566A (en) Turbine nozzle guide vane construction
US3038698A (en) Mechanism for controlling gaseous flow in turbo-machinery
US4311432A (en) Radial seal
US3182955A (en) Construction of turbomachinery blade elements
EP1240411B1 (en) Split ring for tip clearance control
US3938906A (en) Slidable stator seal
US10920618B2 (en) Air seal interface with forward engagement features and active clearance control for a gas turbine engine
US1505647A (en) Packing for elastic-fluid turbines and the like
CA2916710A1 (en) Seals for gas turbine engines
JPS6138102A (en) Cover device for gas turbine power plant
US3519366A (en) Turbine diaphragm seal structure
GB1008526A (en) Axial flow bladed rotor, e.g. for a turbine
US11339722B2 (en) Air seal interface with AFT engagement features and active clearance control for a gas turbine engine
US4875828A (en) Turbo-engine having means for controlling the radial gap
US3389889A (en) Axial flow rotor
US5154575A (en) Thermal blade tip clearance control for gas turbine engines
US2458149A (en) Rotor construction for turbines