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US3836282A - Stator vane support and construction thereof - Google Patents

Stator vane support and construction thereof Download PDF

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Publication number
US3836282A
US3836282A US00345808A US34580873A US3836282A US 3836282 A US3836282 A US 3836282A US 00345808 A US00345808 A US 00345808A US 34580873 A US34580873 A US 34580873A US 3836282 A US3836282 A US 3836282A
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US
United States
Prior art keywords
vane
slot
depressions
sheet metal
construction
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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
US00345808A
Inventor
W Mandelbaum
J Violette
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RTX Corp
Original Assignee
United Aircraft Corp
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Filing date
Publication date
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to US00345808A priority Critical patent/US3836282A/en
Priority to DE19742407960 priority patent/DE2407960A1/en
Priority to CA193,777A priority patent/CA987237A/en
Priority to GB1075174A priority patent/GB1442860A/en
Priority to SE7403581A priority patent/SE390189B/en
Priority to FR7411827A priority patent/FR2223551A1/fr
Priority to IT82808/74A priority patent/IT1010995B/en
Application granted granted Critical
Publication of US3836282A publication Critical patent/US3836282A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • ABSTRACT A deformable and expandable metal support formed from a thin sheet metal mounted between the stator or fixed vane and the wall of the complementary recess formed in the engine casing or shroud provides an interference fit for supporting the vane therein.
  • a plurality of spaced elongated stamped-out depressions spaced chordwise relative to the vane and extending into the slot formed in the support structure carry a leadin ramp and by virtue of press fitting therein said depressions are expanded laterally and deformed and when in the deformed condition provide a stiff zero clearance joint.
  • This invention relates to fixed or stator vanes of the type that are utilized with aircraft engines or propulsors and particularly to means for supporting the vanes to the engine casing or other support member.
  • the problem solved by this invention is the inclusion of means for assuring an interference fit between the vane assembly and the engine case. While the invention will be described in its preferred embodiment as being a stator vane for the compressor of a turbine power plant, it will be understood that this invention is contemplated for use with any fixed vane. Whether the vane is inserted directly in the casing or in a shroud which in turn is supported to the casing, the problems are identical and what is deemed important is that the support adequately withstands the load created by the air loading on the vane.
  • corrugated support absorbs most of the deformation required for a press fit without introducing a prestress in the vane proper.
  • a prestress condition is especially undesirable when lightweight hollow structures of titanium or composite material are to be employed in vane construction.
  • the junction should not be prestressed.
  • the boron composite materials are known for their high stiffness so this problem of prestressing this critical area is even more acute.
  • I have found that I can obviate the problems noted above and provide a means for obtaining an interference fit of the stator vane assembly and prevent prestressing the vane at any point by mounting a metal support on the side at the end of the vane to be inserted in the engine case which support comprises a plurality of stamped-out elongated depressions spaced along the vanes in the chordwise direction which depressions are deformable when fitted into its retaining slot.
  • a still further object of this invention is to provide for a fixed or stator vane assembly support means which comprise a stamped-out sheet metal member extending along the chordwise direction of the vane having a plurality of depression spaced in chordwise direction and deform when inserted into the retaining slot to provide a stiff joint.
  • a still further object of this invention is to provide means for obtaining an interference fit for a fixed vane including a thin metal member having a plurality of de pressions stamped therein which are expandable and deformable when inserted into the retaining slot and is characterized by the fact that it prevents loss of load carrying capacity of airfoil structure, a stiff zero clearance joint remains even at high temperatures and the configuration allows for good flexibility in accomplishing a range of interference fits.
  • FIG. 1 is a perspective view partly in section illustrating a vane in a mounted and another in an unmounted position.
  • FIG. 2 is a sectional view taken along line 2-2 of FIG. ll.
  • FIG. 3 is a sectional view showing the deformation of the metal support when inserted into the slot and
  • FIG. 4 is a view partly in section and partly in elevation showing the configuration of one of the depressions in the metal support.
  • FIGS. 1-4 illustrating the details of this invention.
  • the vane generally illustrated by numeral 10 comprises a support section 12 an airfoil section 14 and a tang l6 and a plurality of them are circumferentially spaced to provide a guide path for the air passing therethrough.
  • a metal sheath 18 may be secured to the leading edge which is generally provided in vanesthat are constructed from a composite material such as Borsic aluminum, boron epoxy and the like.
  • Each vane is supported in either engine casing or shroud member 20 and the annular ring 22.
  • the casing 20 carries a plurality of bosses 24 having a suitable slot 26 formed therein to suitably contour to receive the outboard section of the blade 14. In certain applications as shown in these Figures, it may be desirable to attach a rigid metal member 28 to the top and bottom faces at the support section of the vane 14.
  • the slightly contoured metal support member 30 complements the face of the vane and extends in a chordwise direction of the vane and fits between the space provided between the vane face and the wall of slot 26.
  • a plurality of depressions 32 extending radially outward toward the wall of the slot are stamped in the metal support and are constructed so that they deform and expand in a chordwise direction when inserted into the slot.
  • Rivet holes 34 preferably formed therein are aligned with the rivet holes 36 formed in the boss and restrained from further chordwise expansion by rivet 38 when in the assembled position. Also the rivets prevent the vanes from cocking or rocking edgewise in the slot. Alternatively, the assembly may be drilled and riveted when in place.
  • tangs l6 fit the complementary slot 40 formed in the annular ring member 22. It may be desirable in certain applications to include a similar constraint member in place of the tangs. Also it is contemplated within the scope of the invention that the slots or recesses are grooved to accommodate the depression where the grooves in the configuration would be sized to deform the depression in the metal support.
  • each depression 32 is contoured such that the lead-in end 36 is ramped to serve as a guide and facilitate press fitting the vane assembly into the slot 26.
  • the opposite end 38 is also contoured to take up the load at this end incurred by the blade loading. In the event that the vane is fitted in the slot from the other direction, as would be obvious, this end would become the lead-in end and a similar ramp would be provided.
  • Means for forming a joint for a fixed vane mounted in a shroud said means including a sheet metal member having opposing side surfaces, a plurality of spaced elongated closed ended stamped-out depressions extending radially from one of said side surfaces and the other of said side surfaces being contiguous with the face of said fixed vane on one end, said disc having bass means defining a slot for receiving said one end of the fixed vane, the said one end together with said sheet metal member interference fitted into said slot whereby said depressions expand in a chordwise direction relative to the vane forming with bass means the stiff joint and absorbing the aerodynamic loading.
  • Means for forming a joint as claimed in claim 1 including means for securing said sheet metal to said vane.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A deformable and expandable metal support formed from a thin sheet metal mounted between the stator or fixed vane and the wall of the complementary recess formed in the engine casing or shroud provides an interference fit for supporting the vane therein. A plurality of spaced elongated stamped-out depressions spaced chordwise relative to the vane and extending into the slot formed in the support structure carry a lead-in ramp and by virtue of press fitting therein said depressions are expanded laterally and deformed and when in the deformed condition provide a stiff zero clearance joint.

Description

United States Patent [191 Mandelhaum et a1.
[ STATOR VANE SUPPORT AND CONSTRUCTION THEREOF [75] Inventors: William Mandelbaum, Bloomfield;
John A. Violette, Granby, both of Conn.
[73] Assignee: United Aircraft Corporation, East Hartford, Conn.
[22] Filed: Mar. 28, 1973 [21] Appl. No.: 345,808
[52] US. Cl. 415/217, 416/500 [51] llnt. C1. F0ld 5/10 [58] Fiefld of Search 415/217, 218, 135, 136, 415/137, 190, 189, 191; 416/220; 418/500 [56] References Cited UNITED STATES PATENTS 2,914,300 11/1959 Sayre 415/135 3,291,382 12/1966 Blackhurst et a] 415/217 3,708,242 1/1973 Bruneau et al. 415/217 [11] 3,836,282 [451 Sept. 17,1974
FOREIGN PATENTS OR APPLICATIONS 1,025,421 3/1958 Germany 416/220 Primary Examiner-Henry F. Raduazo Attorney, Agent, or Firm-Norman Friedland 5 7] ABSTRACT A deformable and expandable metal support formed from a thin sheet metal mounted between the stator or fixed vane and the wall of the complementary recess formed in the engine casing or shroud provides an interference fit for supporting the vane therein. A plurality of spaced elongated stamped-out depressions spaced chordwise relative to the vane and extending into the slot formed in the support structure carry a leadin ramp and by virtue of press fitting therein said depressions are expanded laterally and deformed and when in the deformed condition provide a stiff zero clearance joint.
4 Claims, 4 Drawing Figures FATENIED SE? 1 914 SHEET E OF 2 STATOR VANE SUPPORT AND CONSTRUCTION THEREOF BACKGROUND OF THE INVENTION This invention relates to fixed or stator vanes of the type that are utilized with aircraft engines or propulsors and particularly to means for supporting the vanes to the engine casing or other support member.
The problem solved by this invention is the inclusion of means for assuring an interference fit between the vane assembly and the engine case. While the invention will be described in its preferred embodiment as being a stator vane for the compressor of a turbine power plant, it will be understood that this invention is contemplated for use with any fixed vane. Whether the vane is inserted directly in the casing or in a shroud which in turn is supported to the casing, the problems are identical and what is deemed important is that the support adequately withstands the load created by the air loading on the vane.
Most important is that the corrugated support absorbs most of the deformation required for a press fit without introducing a prestress in the vane proper. Such a prestress condition is especially undesirable when lightweight hollow structures of titanium or composite material are to be employed in vane construction.
Heretofore the method of installing the vane, aside from welding or constructing an integral end on it, was to allow a chordwise deformation through the vane proper. The end part of the vane which engaged the slot was required to uncamber, much like a leaf spring loaded at the center of the low-pressure side and resisted at the leading and trailing edges of the high pressure side. Considerable deformation of the airfoil was necessary to absorb variations in tolerances as well as to provide sufficient retention stiffness. This deformation adversely affected the working airfoils of adjacent stations and introduced additional stress at the supporting end of the vane.
Inasmuch as the vane in the assembled condition is tantamount to a cantilever beam and the critical stress area is at the junction point where the supporting'end interfaces with the slot in the casing and obviously is subjected to the high air loadings on the vane, the junction should not be prestressed. The boron composite materials are known for their high stiffness so this problem of prestressing this critical area is even more acute.
I have found that I can obviate the problems noted above and provide a means for obtaining an interference fit of the stator vane assembly and prevent prestressing the vane at any point by mounting a metal support on the side at the end of the vane to be inserted in the engine case which support comprises a plurality of stamped-out elongated depressions spaced along the vanes in the chordwise direction which depressions are deformable when fitted into its retaining slot.
SUMMARY OF THE INVENTION It is an object of this invention to provide for a stator vane assembly means for obtaining an interference fit.
A still further object of this invention is to provide for a fixed or stator vane assembly support means which comprise a stamped-out sheet metal member extending along the chordwise direction of the vane having a plurality of depression spaced in chordwise direction and deform when inserted into the retaining slot to provide a stiff joint.
A still further object of this invention is to provide means for obtaining an interference fit for a fixed vane including a thin metal member having a plurality of de pressions stamped therein which are expandable and deformable when inserted into the retaining slot and is characterized by the fact that it prevents loss of load carrying capacity of airfoil structure, a stiff zero clearance joint remains even at high temperatures and the configuration allows for good flexibility in accomplishing a range of interference fits.
Other features and advantages will be apparent from the specification and claims and from the accompanying drawings which illustrate an embodiment of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view partly in section illustrating a vane in a mounted and another in an unmounted position.
FIG. 2 is a sectional view taken along line 2-2 of FIG. ll.
FIG. 3 is a sectional view showing the deformation of the metal support when inserted into the slot and FIG. 4 is a view partly in section and partly in elevation showing the configuration of one of the depressions in the metal support.
DESCRIPTION OF THE PREFERRED EMBODIMENT Reference is now made to FIGS. 1-4 illustrating the details of this invention. As shown in FIG. 1 the vane generally illustrated by numeral 10 comprises a support section 12 an airfoil section 14 and a tang l6 and a plurality of them are circumferentially spaced to provide a guide path for the air passing therethrough. A metal sheath 18 may be secured to the leading edge which is generally provided in vanesthat are constructed from a composite material such as Borsic aluminum, boron epoxy and the like. Each vane is supported in either engine casing or shroud member 20 and the annular ring 22. The casing 20 carries a plurality of bosses 24 having a suitable slot 26 formed therein to suitably contour to receive the outboard section of the blade 14. In certain applications as shown in these Figures, it may be desirable to attach a rigid metal member 28 to the top and bottom faces at the support section of the vane 14.
In accordance with this invention the slightly contoured metal support member 30 complements the face of the vane and extends in a chordwise direction of the vane and fits between the space provided between the vane face and the wall of slot 26. A plurality of depressions 32 extending radially outward toward the wall of the slot are stamped in the metal support and are constructed so that they deform and expand in a chordwise direction when inserted into the slot. Rivet holes 34 preferably formed therein are aligned with the rivet holes 36 formed in the boss and restrained from further chordwise expansion by rivet 38 when in the assembled position. Also the rivets prevent the vanes from cocking or rocking edgewise in the slot. Alternatively, the assembly may be drilled and riveted when in place.
It will be noted that in this installation tangs l6 fit the complementary slot 40 formed in the annular ring member 22. it may be desirable in certain applications to include a similar constraint member in place of the tangs. Also it is contemplated within the scope of the invention that the slots or recesses are grooved to accommodate the depression where the grooves in the configuration would be sized to deform the depression in the metal support.
As can be seen in FIG. 4 each depression 32 is contoured such that the lead-in end 36 is ramped to serve as a guide and facilitate press fitting the vane assembly into the slot 26. The opposite end 38 is also contoured to take up the load at this end incurred by the blade loading. In the event that the vane is fitted in the slot from the other direction, as would be obvious, this end would become the lead-in end and a similar ramp would be provided.
It should be understood that the invention is not lim ited to the particular embodiments shown and described herein, but that various changes and modifications may be made without departing from the spirit or scope of this novel concept as defined by the following claims.
We claim:
1. Means for forming a joint for a fixed vane mounted in a shroud, said means including a sheet metal member having opposing side surfaces, a plurality of spaced elongated closed ended stamped-out depressions extending radially from one of said side surfaces and the other of said side surfaces being contiguous with the face of said fixed vane on one end, said disc having bass means defining a slot for receiving said one end of the fixed vane, the said one end together with said sheet metal member interference fitted into said slot whereby said depressions expand in a chordwise direction relative to the vane forming with bass means the stiff joint and absorbing the aerodynamic loading.
2. A vane construction as claimed in claim 1 wherein the end of the depression is sized and shaped to define ramp surface to facilitate the insertion of the vane within the slot.
3. Means for forming a joint as claimed in claim 1 including means for securing said sheet metal to said vane.
4. A vane construction as claimed in claim 3 wherein said securing means includes rivets extending through said bass means.

Claims (4)

1. Means for forming a joint for a fixed vane mounted in a shroud, said means including a sheet metal member having opposing side surfaces, a plurality of spaced elongated closed ended stamped-out depressions extending radially from one of said side surfaces and the other of said side surfaces being contiguous with the face of said fixed vane on one end, said disc having bass means defining a slot for receiving said one end of the fixed vane, the said one end together with said sheet metal member interference fitted into said slot whereby said depressions expand in a chordwise direction relative to the vane forming with bass means the stiff joint and absorbing the aerodynamic loading.
2. A vane construction as claimed in claim 1 wherein the end of the depression is sized and shaped to define ramp surface to facilitate the insertion of the vane within the slot.
3. Means for forming a joint as claimed in claim 1 including means for securing said sheet metal to said vane.
4. A vane construction as claimed in claim 3 wherein said securing means includes rivets extending through said bass means.
US00345808A 1973-03-28 1973-03-28 Stator vane support and construction thereof Expired - Lifetime US3836282A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US00345808A US3836282A (en) 1973-03-28 1973-03-28 Stator vane support and construction thereof
DE19742407960 DE2407960A1 (en) 1973-03-28 1974-02-19 STATOR BLADE AND SUPPORT FOR IT
CA193,777A CA987237A (en) 1973-03-28 1974-02-28 Stator vane support and construction thereof
GB1075174A GB1442860A (en) 1973-03-28 1974-03-11 Stator vane construction
SE7403581A SE390189B (en) 1973-03-28 1974-03-18 STATOR PLATE FIXING
FR7411827A FR2223551A1 (en) 1973-03-28 1974-03-22
IT82808/74A IT1010995B (en) 1973-03-28 1974-03-27 SUPPORT FOR TURBINE MOTOR STATOR BLADES AND ITS CONSTRUCTION

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US00345808A US3836282A (en) 1973-03-28 1973-03-28 Stator vane support and construction thereof

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US3836282A true US3836282A (en) 1974-09-17

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CA (1) CA987237A (en)
DE (1) DE2407960A1 (en)
FR (1) FR2223551A1 (en)
GB (1) GB1442860A (en)
IT (1) IT1010995B (en)
SE (1) SE390189B (en)

Cited By (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3966353A (en) * 1975-02-21 1976-06-29 Westinghouse Electric Corporation Ceramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
FR2522362A1 (en) * 1982-02-26 1983-09-02 Gen Electric BUILDING ELEMENT OF AUBES
US4452564A (en) * 1981-11-09 1984-06-05 The Garrett Corporation Stator vane assembly and associated methods
US4695225A (en) * 1983-08-30 1987-09-22 Bbc Brown, Boveri & Company, Limited Axial swirl body for generating rotary flows
FR2606071A1 (en) * 1986-10-29 1988-05-06 Snecma Stator stage and turbine engine compressor comprising it
FR2671140A1 (en) * 1990-12-27 1992-07-03 Snecma Guide vanes for a turbo machine compressor
US5174715A (en) * 1990-12-13 1992-12-29 General Electric Company Turbine nozzle
US5180282A (en) * 1991-09-27 1993-01-19 General Electric Company Gas turbine engine structural frame with multi-yoke attachment of struts to outer casing
US5292227A (en) * 1992-12-10 1994-03-08 General Electric Company Turbine frame
US5411368A (en) * 1993-11-08 1995-05-02 Allied-Signal Inc. Ceramic-to-metal stator vane assembly with braze
US5438756A (en) * 1993-12-17 1995-08-08 General Electric Company Method for assembling a turbine frame assembly
US5474419A (en) * 1992-12-30 1995-12-12 Reluzco; George Flowpath assembly for a turbine diaphragm and methods of manufacture
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
US5586864A (en) * 1994-07-27 1996-12-24 General Electric Company Turbine nozzle diaphragm and method of assembly
US5704762A (en) * 1993-11-08 1998-01-06 Alliedsignal Inc. Ceramic-to-metal stator vane assembly
US6000906A (en) * 1997-09-12 1999-12-14 Alliedsignal Inc. Ceramic airfoil
US6409472B1 (en) * 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
US6439841B1 (en) * 2000-04-29 2002-08-27 General Electric Company Turbine frame assembly
US7097432B1 (en) * 2000-07-19 2006-08-29 Honeywell International, Inc. Sliding vane turbocharger with graduated vanes
US20090214349A1 (en) * 2008-02-22 2009-08-27 Siemens Power Generation, Inc. Airfoil Structure Shim
US20100061845A1 (en) * 2006-10-28 2010-03-11 Daniela Turzing Guiding device of a flow machine and guide vane for such a guiding device
US20100183435A1 (en) * 2008-09-18 2010-07-22 Campbell Christian X Gas Turbine Vane Platform Element
US20110081240A1 (en) * 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Fabricated gas turbine vane ring
US20130205800A1 (en) * 2012-02-10 2013-08-15 Richard Ivakitch Vane assemblies for gas turbine engines
EP2434101A3 (en) * 2010-09-22 2014-01-01 Rolls-Royce plc A damped assembly
US20140255177A1 (en) * 2013-03-07 2014-09-11 Rolls-Royce Canada, Ltd. Outboard insertion system of variable guide vanes or stationary vanes
US20140356158A1 (en) * 2013-05-28 2014-12-04 Pratt & Whitney Canada Corp. Gas turbine engine vane assembly and method of mounting same
EP2479383A3 (en) * 2011-01-20 2015-08-12 United Technologies Corporation Gas Turbine Engine Stator Vane Assembly
US20160138413A1 (en) * 2014-11-18 2016-05-19 Techspace Aero S.A. Internal Shroud for a Compressor of an Axial-Flow Turbomachine
US20180209303A1 (en) * 2017-01-26 2018-07-26 General Electric Company Alignment apparatus for coupling diaphragms of turbines
US20180334910A1 (en) * 2017-05-19 2018-11-22 General Electric Company Turbomachine cooling system
EP3431709A1 (en) * 2017-07-17 2019-01-23 Rolls-Royce Corporation Apparatus for airfoil leading edge protection
US11286798B2 (en) * 2019-08-20 2022-03-29 Rolls-Royce Corporation Airfoil assembly with ceramic matrix composite parts and load-transfer features
CN114278391A (en) * 2021-12-29 2022-04-05 河北国源电气股份有限公司 Static blade group for steam turbine of installation close-fitting
US11346246B2 (en) * 2017-12-01 2022-05-31 Siemens Energy, Inc. Brazed in heat transfer feature for cooled turbine components

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2220034B (en) * 1988-06-22 1992-12-02 Rolls Royce Plc Aerodynamic loading in gas turbine engines
US5332360A (en) * 1993-09-08 1994-07-26 General Electric Company Stator vane having reinforced braze joint

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1025421B (en) * 1955-10-31 1958-03-06 Maschf Augsburg Nuernberg Ag Fastening of blades made of sproated material in a metallic blade carrier
US2914300A (en) * 1955-12-22 1959-11-24 Gen Electric Nozzle vane support for turbines
US3291382A (en) * 1964-05-08 1966-12-13 Rolls Royce Bladed structure, for example, for a gas turbine engine compressor
US3708242A (en) * 1969-12-01 1973-01-02 Snecma Supporting structure for the blades of turbomachines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1025421B (en) * 1955-10-31 1958-03-06 Maschf Augsburg Nuernberg Ag Fastening of blades made of sproated material in a metallic blade carrier
US2914300A (en) * 1955-12-22 1959-11-24 Gen Electric Nozzle vane support for turbines
US3291382A (en) * 1964-05-08 1966-12-13 Rolls Royce Bladed structure, for example, for a gas turbine engine compressor
US3708242A (en) * 1969-12-01 1973-01-02 Snecma Supporting structure for the blades of turbomachines

Cited By (50)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3966353A (en) * 1975-02-21 1976-06-29 Westinghouse Electric Corporation Ceramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
US4452564A (en) * 1981-11-09 1984-06-05 The Garrett Corporation Stator vane assembly and associated methods
FR2522362A1 (en) * 1982-02-26 1983-09-02 Gen Electric BUILDING ELEMENT OF AUBES
US4695225A (en) * 1983-08-30 1987-09-22 Bbc Brown, Boveri & Company, Limited Axial swirl body for generating rotary flows
FR2606071A1 (en) * 1986-10-29 1988-05-06 Snecma Stator stage and turbine engine compressor comprising it
US5174715A (en) * 1990-12-13 1992-12-29 General Electric Company Turbine nozzle
FR2671140A1 (en) * 1990-12-27 1992-07-03 Snecma Guide vanes for a turbo machine compressor
US5180282A (en) * 1991-09-27 1993-01-19 General Electric Company Gas turbine engine structural frame with multi-yoke attachment of struts to outer casing
US5292227A (en) * 1992-12-10 1994-03-08 General Electric Company Turbine frame
US5474419A (en) * 1992-12-30 1995-12-12 Reluzco; George Flowpath assembly for a turbine diaphragm and methods of manufacture
US5704762A (en) * 1993-11-08 1998-01-06 Alliedsignal Inc. Ceramic-to-metal stator vane assembly
US5411368A (en) * 1993-11-08 1995-05-02 Allied-Signal Inc. Ceramic-to-metal stator vane assembly with braze
US5438756A (en) * 1993-12-17 1995-08-08 General Electric Company Method for assembling a turbine frame assembly
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
US5586864A (en) * 1994-07-27 1996-12-24 General Electric Company Turbine nozzle diaphragm and method of assembly
US6000906A (en) * 1997-09-12 1999-12-14 Alliedsignal Inc. Ceramic airfoil
US6409472B1 (en) * 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
EP1626163A2 (en) 1999-08-09 2006-02-15 United Technologies Corporation Clip member for a stator assembly
EP1626163A3 (en) * 1999-08-09 2008-10-29 United Technologies Corporation Clip member for a stator assembly
US6439841B1 (en) * 2000-04-29 2002-08-27 General Electric Company Turbine frame assembly
US7097432B1 (en) * 2000-07-19 2006-08-29 Honeywell International, Inc. Sliding vane turbocharger with graduated vanes
US20100061845A1 (en) * 2006-10-28 2010-03-11 Daniela Turzing Guiding device of a flow machine and guide vane for such a guiding device
US8075265B2 (en) * 2006-10-28 2011-12-13 Man Diesel & Turbo Se Guiding device of a flow machine and guide vane for such a guiding device
US20090214349A1 (en) * 2008-02-22 2009-08-27 Siemens Power Generation, Inc. Airfoil Structure Shim
US8210819B2 (en) * 2008-02-22 2012-07-03 Siemens Energy, Inc. Airfoil structure shim
US20100183435A1 (en) * 2008-09-18 2010-07-22 Campbell Christian X Gas Turbine Vane Platform Element
US8251652B2 (en) * 2008-09-18 2012-08-28 Siemens Energy, Inc. Gas turbine vane platform element
US8469661B2 (en) 2009-10-01 2013-06-25 Pratt & Whitney Canada Corp. Fabricated gas turbine vane ring
US20110081240A1 (en) * 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Fabricated gas turbine vane ring
EP2434101A3 (en) * 2010-09-22 2014-01-01 Rolls-Royce plc A damped assembly
US9074478B2 (en) 2010-09-22 2015-07-07 Rolls-Royce Plc Damped assembly
EP2479383A3 (en) * 2011-01-20 2015-08-12 United Technologies Corporation Gas Turbine Engine Stator Vane Assembly
US20130205800A1 (en) * 2012-02-10 2013-08-15 Richard Ivakitch Vane assemblies for gas turbine engines
US9951639B2 (en) * 2012-02-10 2018-04-24 Pratt & Whitney Canada Corp. Vane assemblies for gas turbine engines
US9777584B2 (en) * 2013-03-07 2017-10-03 Rolls-Royce Plc Outboard insertion system of variable guide vanes or stationary vanes
US20140255177A1 (en) * 2013-03-07 2014-09-11 Rolls-Royce Canada, Ltd. Outboard insertion system of variable guide vanes or stationary vanes
US20140356158A1 (en) * 2013-05-28 2014-12-04 Pratt & Whitney Canada Corp. Gas turbine engine vane assembly and method of mounting same
US9840929B2 (en) * 2013-05-28 2017-12-12 Pratt & Whitney Canada Corp. Gas turbine engine vane assembly and method of mounting same
US10113439B2 (en) * 2014-11-18 2018-10-30 Safran Aero Boosters Sa Internal shroud for a compressor of an axial-flow turbomachine
US20160138413A1 (en) * 2014-11-18 2016-05-19 Techspace Aero S.A. Internal Shroud for a Compressor of an Axial-Flow Turbomachine
US10378383B2 (en) * 2017-01-26 2019-08-13 General Electric Company Alignment apparatus for coupling diaphragms of turbines
US20180209303A1 (en) * 2017-01-26 2018-07-26 General Electric Company Alignment apparatus for coupling diaphragms of turbines
US20180334910A1 (en) * 2017-05-19 2018-11-22 General Electric Company Turbomachine cooling system
US10392945B2 (en) * 2017-05-19 2019-08-27 General Electric Company Turbomachine cooling system
EP3431709A1 (en) * 2017-07-17 2019-01-23 Rolls-Royce Corporation Apparatus for airfoil leading edge protection
US10612386B2 (en) * 2017-07-17 2020-04-07 Rolls-Royce Corporation Apparatus for airfoil leading edge protection
US11346246B2 (en) * 2017-12-01 2022-05-31 Siemens Energy, Inc. Brazed in heat transfer feature for cooled turbine components
US11286798B2 (en) * 2019-08-20 2022-03-29 Rolls-Royce Corporation Airfoil assembly with ceramic matrix composite parts and load-transfer features
CN114278391A (en) * 2021-12-29 2022-04-05 河北国源电气股份有限公司 Static blade group for steam turbine of installation close-fitting
CN114278391B (en) * 2021-12-29 2024-04-19 河北国源电气股份有限公司 Stator blade group for turbine with tight fit installation

Also Published As

Publication number Publication date
DE2407960A1 (en) 1974-10-10
IT1010995B (en) 1977-01-20
CA987237A (en) 1976-04-13
FR2223551A1 (en) 1974-10-25
SE390189B (en) 1976-12-06
GB1442860A (en) 1976-07-14

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