US3778184A - Vane damping - Google Patents
Vane damping Download PDFInfo
- Publication number
- US3778184A US3778184A US00265413A US3778184DA US3778184A US 3778184 A US3778184 A US 3778184A US 00265413 A US00265413 A US 00265413A US 3778184D A US3778184D A US 3778184DA US 3778184 A US3778184 A US 3778184A
- Authority
- US
- United States
- Prior art keywords
- vanes
- vane
- shroud
- damping
- wire mesh
- 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
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/04—Antivibration arrangements
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/501—Elasticity
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/614—Fibres or filaments
Definitions
- Damping has been accomplished by positioning a thermoplastic or thermosetting material between the end of the vane and the supporting shroud or around the vane externally of the shroud with the damping material functioning as a bond between the vane and the shroud. Heat may be required in placing the material in the desired position around the vane ends and in some cases heat may be essential in curing the thermosetting material.
- a feature of the present invention is a damping structure which requires no heating of the device or the material. Another feature is a damping structure in which the effectiveness of the damping may be controlled by more or less compressing the damping material prior to or during installation. Another feature is the damping of vane vibration by a material of the felt metal, steel wool or braided or knit wire type.
- the row of vanes are secured to the inner shroud and extend loosely through slots in the outer shroud with the vane ends surrounded by damping material of the felt metal, steel wool or braided or knit wire type thus forming a damper for vane vibration.
- This material is different in structure and function from other damping material in that it is a resilient fibrous material with a significant porosity.
- This material is in contact with the sides of the vane adjacent to the ends of the vanes and may also be in contact with the outer ends of each of the vanes if so desired.
- the damping material is positioned between the shroud and a surrounding cover plate that holds it in position to accomplish the desired damping.
- FIG. 1 is an axial sectional viewthrough a vane assembly showing the damping materials therein.
- damping FIG. 2 is a fragmentary sectional view along the line 2-2 of FIG. 1.
- a row of vanes 2 only one of which is shown in FIG. I are supported at their inner ends by an inner shroud ring 4 the vanes being brazed or welded or otherwise secured in slots 6 in this inner shroud ring.
- Each of the vanes extends outwardly through a slot 8 in the outer shroud ring 10 and the outer end of the vane extends beyond the outer surface of the shroud ring as shown.
- the shroud ring 10 is preferably somewhat U-shaped in cross section having outwardly projecting flanges l2 and 14 with laterally projecting flange rings 16 and 18 thereon.
- the outer edges of the rings 16 and 1 8 may have attachment flanges 20 and 22 for securing the adjacent stages of compressor vanes thereto.
- each vane is received in a porous compressible pad 24 of felt metal, stainless steel wool, braided wire or knit wire which encircles the vane end tightly and extends over the tip of the vane.
- a sheet metal cover 26 attached as by rivets 28 to the shroud ring holds the damping material in place and may serve to preload the material against the vanes and acts as a seal.
- the compartment defined between the shroud ring 10 and the cover 26 is a fixed dimension within which the damping pad is compressed.
- the damping material may extend over a plurality of vanes or there may be a separate damping pad for each of the vane ends. In either event the cover plate 26 holds the pads in position and may be utilized to apply a predetermined load on the damping material thereby to control the effective damping action. It may be desirable to form the pad with a notch 30, F IG. 2, to receive the end of the vane although this :may be unnecessary in many instances depending on the length that the vane projects beyond the shroud ring and the amount of damping pressure that is to be applied to the end of the vane by the damping material.
- a form of pad that has proved to be satisfactory for this purpose is a porous stainless steel single filament wire pad since it will be effective for a longer period of time at the hot end of a multistage axial flow compressor.
- Other wire pad structures in which the wires are feathered together are equally usable. It will be understood that the amount that the pad is compressed thereby reducing the porosity will determine the effectiveness of the damping action on the vane end. It should be noted that no particular preparation is necessary for the vane end since the wire pad is not attached to the vane positively in any way. It may be desirable to provide notches 32 and 34 at the leading and trailing edges of the vane at its outerend since this arrangement will serve to provide a broader surface for damping vibrations chordwise of the vane.
- a turbine vane assembly including a row of turbine vanes extending in a generally radial direction about an axis
- a turbine vane assembly as in claim 1 in wire mesh is in contact with both the sides and the end of each of the vanes.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Damping of compressor or turbine vanes in the supporting shroud is accomplished by surrounding one end of the vane with a damping material of the steel wool or felt metal type held in contact with the shroud in which the vane is loosely supported.
Description
United States Patent 11 1 1111 3,778,184
Wood 1 Dec. 11, 1973 1 VANE DAMPING 3,519,222 7/1970 Davis 415/174 3,071,346 1/1963 Broffit r 415/137 [751 Glasmnbury, 3,556,735 11/1963 Epelman 60/297 Conn.
[73] Ass1gnee: United Aircraft Corporation, East Primary Examiner camon R cmyle Hartford, Conn.
Assistant Examiner-Louis J. Casaregola [22] Filed: June 22, 1972 Att0rr7ey-Charles A. Warren [21] Appl. No.: 265,413
[52] 11.8. C1. 415/174, 415/191 [57] ABSTRACT W [511 E Fold 11/08 Fold 1/02 Fold 9/00 Damping of compressor or turbine vanes in the sup- [58] Fleld 01 Search 415/174, 219, 136, porting Shroud is accomplished by surrounding one 415/137 191; 416/190 500 end of the vane with a damping material of the steel wool or felt metal type held in contact with the shroud [56] References cued in which the vane is loosely supported. 1
UNITED STATES PATENTS 2,952,442 9/1960 Warnken 415/174 4 Claims, 2 Drawing Figures 'PAIENIEnnm 1 ma Z? M XX VANE DAMPING BACKGROUND OF THE INVENTION This invention relates to damping the vanes in a compressor or turbine.
Damping has been accomplished by positioning a thermoplastic or thermosetting material between the end of the vane and the supporting shroud or around the vane externally of the shroud with the damping material functioning as a bond between the vane and the shroud. Heat may be required in placing the material in the desired position around the vane ends and in some cases heat may be essential in curing the thermosetting material.
A feature of the present invention is a damping structure which requires no heating of the device or the material. Another feature is a damping structure in which the effectiveness of the damping may be controlled by more or less compressing the damping material prior to or during installation. Another feature is the damping of vane vibration by a material of the felt metal, steel wool or braided or knit wire type.
According to the present invention the row of vanes are secured to the inner shroud and extend loosely through slots in the outer shroud with the vane ends surrounded by damping material of the felt metal, steel wool or braided or knit wire type thus forming a damper for vane vibration. This material is different in structure and function from other damping material in that it is a resilient fibrous material with a significant porosity. This material is in contact with the sides of the vane adjacent to the ends of the vanes and may also be in contact with the outer ends of each of the vanes if so desired. The damping material is positioned between the shroud and a surrounding cover plate that holds it in position to accomplish the desired damping.
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 an axial sectional viewthrough a vane assembly showing the damping materials therein. damping FIG. 2 is a fragmentary sectional view along the line 2-2 of FIG. 1.
DESCRIPTION OF THE PREFERRED EMBODIMENT A row of vanes 2 only one of which is shown in FIG. I are supported at their inner ends by an inner shroud ring 4 the vanes being brazed or welded or otherwise secured in slots 6 in this inner shroud ring.
Each of the vanes extends outwardly through a slot 8 in the outer shroud ring 10 and the outer end of the vane extends beyond the outer surface of the shroud ring as shown. The shroud ring 10 is preferably somewhat U-shaped in cross section having outwardly projecting flanges l2 and 14 with laterally projecting flange rings 16 and 18 thereon. The outer edges of the rings 16 and 1 8 may have attachment flanges 20 and 22 for securing the adjacent stages of compressor vanes thereto.
The outer end of each vane is received in a porous compressible pad 24 of felt metal, stainless steel wool, braided wire or knit wire which encircles the vane end tightly and extends over the tip of the vane. A sheet metal cover 26 attached as by rivets 28 to the shroud ring holds the damping material in place and may serve to preload the material against the vanes and acts as a seal. The compartment defined between the shroud ring 10 and the cover 26 is a fixed dimension within which the damping pad is compressed. When the vane vibrates energy is dissipated at the contact surface of the vane and damper and internally within the damper. This arrangement requires no structural restraint on the outer end of the vane with respect to the shroud and serves effectively to reduce vibratory stress levels.
The damping material may extend over a plurality of vanes or there may be a separate damping pad for each of the vane ends. In either event the cover plate 26 holds the pads in position and may be utilized to apply a predetermined load on the damping material thereby to control the effective damping action. It may be desirable to form the pad with a notch 30, F IG. 2, to receive the end of the vane although this :may be unnecessary in many instances depending on the length that the vane projects beyond the shroud ring and the amount of damping pressure that is to be applied to the end of the vane by the damping material.
A form of pad that has proved to be satisfactory for this purpose is a porous stainless steel single filament wire pad since it will be effective for a longer period of time at the hot end of a multistage axial flow compressor. Other wire pad structures in which the wires are feathered together are equally usable. It will be understood that the amount that the pad is compressed thereby reducing the porosity will determine the effectiveness of the damping action on the vane end. It should be noted that no particular preparation is necessary for the vane end since the wire pad is not attached to the vane positively in any way. It may be desirable to provide notches 32 and 34 at the leading and trailing edges of the vane at its outerend since this arrangement will serve to provide a broader surface for damping vibrations chordwise of the vane.
I claim:
1. A turbine vane assembly including a row of turbine vanes extending in a generally radial direction about an axis,
an inner shroud to which the inner ends of the vanes are secured,
an outer shroud having openings therein through which the outer ends of the vanes project,
a porous wire mesh fabric forming a compressible pad surrounding and receiving therein the outer end of each vane on the outer side of the outer shroud for damping purposes, and
a band surrounding said outer shroud and overlying the outer ends of the vanes, said hand holding the wire mesh fabric in position, said band being se cured to said outer shroud.
2. A turbine vane assembly as in claim 1 in which said wire meash fabric is an open work material made up of a plurality of metallic wires feathered together to form a compressible mass.
3. A turbine vane assembly as in claim 1 in which said wire mesh extends around substantially the entire periphery of the outer shroud.
4. A turbine vane assembly as in claim 1 in wire mesh is in contact with both the sides and the end of each of the vanes.
I t 4 Q I which said I mg? l a v UNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION Patent No 3,778,184 Dated December 11, 1973 n flslDonald H. Wood It is certified that error appears in theabove-identified patent and that said Letters Batent are hereby corrected as shown below:
Column 1, line 32, delete "may" line 32, delete "be" and insert --desirably-- lines 44-45, delete "damping" second 7 occurrence 7 Column 2, line 30, change "feathered' to --felted-- line 32, delete "thereb y reducing the porosity" line 58, change Y'meas h" to -n1esh-- line 59, 1 change "feathered" to --:Eelted-- Signed and sealed this 21st day of May 1971+.
(SEAL) Attest: I
'0. MARSHALL DAM Commissioner of Patents EQWAEPW QL Attesting Officer
Claims (4)
1. A turbine vane assembly including a row of turbine vanes extending in a generally radial direction about an axis, an inner shroud to which the inner ends of the vanes are secured, an outer shroud having openings therein through which the outer ends of the vanes project, a porous wire mesh fabric forming a compressible pad surrounding and receiving therein the outer end of each vane on the outer side of the outer shroud for damping purposes, and a band surrounding said outer shroud and overlying the outer ends of the vanes, said band holding the wire mesh fabric in position, said band being secured to said outer shroud.
2. A turbine vane assembly as in claim 1 in which said wire meash fabric is an open work material made up of a plurality of metallic wires feathered together to form a compressible mass.
3. A turbine vane assembly as in claim 1 in which said wire mesh extends around substantially the entire periphery of the outer shroud.
4. A turbine vane assembly as in claim 1 in which said wire mesh is in contact with both the sides and the end of each of the vanes.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US26541372A | 1972-06-22 | 1972-06-22 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3778184A true US3778184A (en) | 1973-12-11 |
Family
ID=23010346
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US00265413A Expired - Lifetime US3778184A (en) | 1972-06-22 | 1972-06-22 | Vane damping |
Country Status (2)
Country | Link |
---|---|
US (1) | US3778184A (en) |
AU (1) | AU6347773A (en) |
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3932056A (en) * | 1973-09-27 | 1976-01-13 | Barry Wright Corporation | Vane damping |
US4285633A (en) * | 1979-10-26 | 1981-08-25 | The United States Of America As Represented By The Secretary Of The Air Force | Broad spectrum vibration damper assembly fixed stator vanes of axial flow compressor |
US4305696A (en) * | 1979-03-14 | 1981-12-15 | Rolls-Royce Limited | Stator vane assembly for a gas turbine engine |
US4422648A (en) * | 1982-06-17 | 1983-12-27 | United Technologies Corporation | Ceramic faced outer air seal for gas turbine engines |
US4541776A (en) * | 1982-09-01 | 1985-09-17 | Schoen Christian O | Centrifugal blower for hot fluids |
US4989886A (en) * | 1988-12-30 | 1991-02-05 | Textron Inc. | Braided filamentary sealing element |
US5029875A (en) * | 1989-07-07 | 1991-07-09 | Textron Inc. | Fluid seal structure |
US5074752A (en) * | 1990-08-06 | 1991-12-24 | General Electric Company | Gas turbine outlet guide vane mounting assembly |
US5181827A (en) * | 1981-12-30 | 1993-01-26 | Rolls-Royce Plc | Gas turbine engine shroud ring mounting |
US5300178A (en) * | 1990-02-06 | 1994-04-05 | Soltech Inc. | Insulation arrangement for machinery |
US5411370A (en) * | 1994-08-01 | 1995-05-02 | United Technologies Corporation | Vibration damping shroud for a turbomachine vane |
EP1197323A1 (en) * | 2000-10-10 | 2002-04-17 | Material Sciences Corporation | Metal felt laminate structures |
US6619917B2 (en) * | 2000-12-19 | 2003-09-16 | United Technologies Corporation | Machined fan exit guide vane attachment pockets for use in a gas turbine |
US20070140854A1 (en) * | 2005-12-15 | 2007-06-21 | Rolls-Royce Plc | Vane arrangement and a method of making vane arrangement |
US20070183891A1 (en) * | 2006-01-11 | 2007-08-09 | Evans Dale E | Guide vane arrangements for gas turbine engines |
EP1764481A3 (en) * | 2005-09-19 | 2008-12-17 | General Electric Company | Stator vane with ceramic airfoil and metallic platforms |
WO2010094277A3 (en) * | 2009-02-23 | 2011-06-23 | Mtu Aero Engines Gmbh | Gas turbine machine comprising a damped blade cluster |
US20110302912A1 (en) * | 2010-06-09 | 2011-12-15 | Jewess Gordon F | Compressor diffuser vane damper |
US8157507B1 (en) * | 2010-01-19 | 2012-04-17 | Florida Turbine Technologies, Inc. | Damped stator assembly |
EP2243961A3 (en) * | 2009-04-22 | 2013-10-30 | Pratt & Whitney Canada Corp. | Vane assembly with removable vanes |
WO2014011268A2 (en) * | 2012-07-09 | 2014-01-16 | United Technologies Corporation | Thin metal duct damper |
US20140030085A1 (en) * | 2012-07-30 | 2014-01-30 | William R. Edwards | Compliant assembly |
EP2977558A1 (en) * | 2014-07-22 | 2016-01-27 | Rolls-Royce plc | An annular support, a casing, and vane assembly |
US20160363002A1 (en) * | 2015-06-15 | 2016-12-15 | Ansaldo Energia Ip Uk Limited | Damping means for components in a turbomachine and method for assembling said damping means |
US10132429B2 (en) * | 2014-06-13 | 2018-11-20 | Siemens Aktiengesellschaft | Connecting clip having a metal wire mat as a damping element |
FR3092137A1 (en) * | 2019-01-30 | 2020-07-31 | Safran Aircraft Engines | Turbomachine stator sector with high stress areas |
US11236615B1 (en) * | 2020-09-01 | 2022-02-01 | Solar Turbines Incorporated | Stator assembly for compressor mid-plane rotor balancing and sealing in gas turbine engine |
WO2022167373A1 (en) | 2021-02-02 | 2022-08-11 | Safran Aero Boosters | Stator vane assembly for an aircraft turbine engine compressor |
US11519276B1 (en) * | 2022-01-12 | 2022-12-06 | General Electric Company | Vibration damping system for turbine blade or nozzle, retention system therefor, and method of assembly |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2952442A (en) * | 1957-05-28 | 1960-09-13 | Studebaker Packard Corp | Rotating shroud |
US3071346A (en) * | 1960-06-21 | 1963-01-01 | Wilgus S Broffitt | Turbine nozzle |
US3519282A (en) * | 1966-03-11 | 1970-07-07 | Gen Electric | Abradable material seal |
US3556735A (en) * | 1967-06-23 | 1971-01-19 | Jacobo Epelman | Muffler adapted to purify the exhaust gases of internal combustion engines |
-
1972
- 1972-06-22 US US00265413A patent/US3778184A/en not_active Expired - Lifetime
-
1973
- 1973-12-11 AU AU63477/73A patent/AU6347773A/en not_active Expired
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2952442A (en) * | 1957-05-28 | 1960-09-13 | Studebaker Packard Corp | Rotating shroud |
US3071346A (en) * | 1960-06-21 | 1963-01-01 | Wilgus S Broffitt | Turbine nozzle |
US3519282A (en) * | 1966-03-11 | 1970-07-07 | Gen Electric | Abradable material seal |
US3556735A (en) * | 1967-06-23 | 1971-01-19 | Jacobo Epelman | Muffler adapted to purify the exhaust gases of internal combustion engines |
Cited By (42)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3932056A (en) * | 1973-09-27 | 1976-01-13 | Barry Wright Corporation | Vane damping |
US4305696A (en) * | 1979-03-14 | 1981-12-15 | Rolls-Royce Limited | Stator vane assembly for a gas turbine engine |
US4285633A (en) * | 1979-10-26 | 1981-08-25 | The United States Of America As Represented By The Secretary Of The Air Force | Broad spectrum vibration damper assembly fixed stator vanes of axial flow compressor |
US5181827A (en) * | 1981-12-30 | 1993-01-26 | Rolls-Royce Plc | Gas turbine engine shroud ring mounting |
US4422648A (en) * | 1982-06-17 | 1983-12-27 | United Technologies Corporation | Ceramic faced outer air seal for gas turbine engines |
US4541776A (en) * | 1982-09-01 | 1985-09-17 | Schoen Christian O | Centrifugal blower for hot fluids |
US4989886A (en) * | 1988-12-30 | 1991-02-05 | Textron Inc. | Braided filamentary sealing element |
US5029875A (en) * | 1989-07-07 | 1991-07-09 | Textron Inc. | Fluid seal structure |
US5300178A (en) * | 1990-02-06 | 1994-04-05 | Soltech Inc. | Insulation arrangement for machinery |
US5074752A (en) * | 1990-08-06 | 1991-12-24 | General Electric Company | Gas turbine outlet guide vane mounting assembly |
US5411370A (en) * | 1994-08-01 | 1995-05-02 | United Technologies Corporation | Vibration damping shroud for a turbomachine vane |
WO1996004468A1 (en) * | 1994-08-01 | 1996-02-15 | United Technologies Corporation | Vibration damping shroud for a turbomachine vane |
EP1197323A1 (en) * | 2000-10-10 | 2002-04-17 | Material Sciences Corporation | Metal felt laminate structures |
US6465110B1 (en) | 2000-10-10 | 2002-10-15 | Material Sciences Corporation | Metal felt laminate structures |
US6619917B2 (en) * | 2000-12-19 | 2003-09-16 | United Technologies Corporation | Machined fan exit guide vane attachment pockets for use in a gas turbine |
EP1764481A3 (en) * | 2005-09-19 | 2008-12-17 | General Electric Company | Stator vane with ceramic airfoil and metallic platforms |
US20070140854A1 (en) * | 2005-12-15 | 2007-06-21 | Rolls-Royce Plc | Vane arrangement and a method of making vane arrangement |
US7837444B2 (en) * | 2005-12-15 | 2010-11-23 | Rolls-Royce Plc | Vane arrangement and a method of making vane arrangement |
US20070183891A1 (en) * | 2006-01-11 | 2007-08-09 | Evans Dale E | Guide vane arrangements for gas turbine engines |
US7753648B2 (en) * | 2006-01-11 | 2010-07-13 | Rolls-Royce Plc | Guide vane arrangements for gas turbine engines |
WO2010094277A3 (en) * | 2009-02-23 | 2011-06-23 | Mtu Aero Engines Gmbh | Gas turbine machine comprising a damped blade cluster |
EP2243961A3 (en) * | 2009-04-22 | 2013-10-30 | Pratt & Whitney Canada Corp. | Vane assembly with removable vanes |
US8157507B1 (en) * | 2010-01-19 | 2012-04-17 | Florida Turbine Technologies, Inc. | Damped stator assembly |
US8834097B2 (en) * | 2010-06-09 | 2014-09-16 | Hamilton Sundstrand Corporation | Compressor diffuser vane damper |
US20110302912A1 (en) * | 2010-06-09 | 2011-12-15 | Jewess Gordon F | Compressor diffuser vane damper |
WO2014011268A2 (en) * | 2012-07-09 | 2014-01-16 | United Technologies Corporation | Thin metal duct damper |
WO2014011268A3 (en) * | 2012-07-09 | 2014-03-27 | United Technologies Corporation | Thin metal duct damper |
US9447693B2 (en) * | 2012-07-30 | 2016-09-20 | United Technologies Corporation | Compliant assembly |
US20140030085A1 (en) * | 2012-07-30 | 2014-01-30 | William R. Edwards | Compliant assembly |
US10132429B2 (en) * | 2014-06-13 | 2018-11-20 | Siemens Aktiengesellschaft | Connecting clip having a metal wire mat as a damping element |
EP2977558A1 (en) * | 2014-07-22 | 2016-01-27 | Rolls-Royce plc | An annular support, a casing, and vane assembly |
US20160363002A1 (en) * | 2015-06-15 | 2016-12-15 | Ansaldo Energia Ip Uk Limited | Damping means for components in a turbomachine and method for assembling said damping means |
US10570771B2 (en) * | 2015-06-15 | 2020-02-25 | General Electric Technology Gmbh | Damping means for components in a turbomachine and method for assembling said damping means |
FR3092137A1 (en) * | 2019-01-30 | 2020-07-31 | Safran Aircraft Engines | Turbomachine stator sector with high stress areas |
WO2020157405A1 (en) * | 2019-01-30 | 2020-08-06 | Safran Aircraft Engines | Turbomachine stator sector having flexible regions subjected to high stress |
CN113366192A (en) * | 2019-01-30 | 2021-09-07 | 赛峰航空器发动机 | Turbine stator sector with compliant regions subject to high stresses |
US11767767B2 (en) | 2019-01-30 | 2023-09-26 | Safran Aircraft Engines | Turbomachine stator sector having flexible regions subjected to high stress |
CN113366192B (en) * | 2019-01-30 | 2024-04-02 | 赛峰航空器发动机 | Turbine stator sector with flexible regions subjected to high stresses |
US11236615B1 (en) * | 2020-09-01 | 2022-02-01 | Solar Turbines Incorporated | Stator assembly for compressor mid-plane rotor balancing and sealing in gas turbine engine |
WO2022167373A1 (en) | 2021-02-02 | 2022-08-11 | Safran Aero Boosters | Stator vane assembly for an aircraft turbine engine compressor |
BE1029074B1 (en) * | 2021-02-02 | 2022-08-29 | Safran Aero Boosters | AIRCRAFT TURBOMACHINE COMPRESSOR RECTIFIER ASSEMBLY |
US11519276B1 (en) * | 2022-01-12 | 2022-12-06 | General Electric Company | Vibration damping system for turbine blade or nozzle, retention system therefor, and method of assembly |
Also Published As
Publication number | Publication date |
---|---|
AU6347773A (en) | 1975-06-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3778184A (en) | Vane damping | |
US4305696A (en) | Stator vane assembly for a gas turbine engine | |
US3784320A (en) | Method and means for retaining ceramic turbine blades | |
US3640357A (en) | Acoustic linings | |
US4721434A (en) | Damping means for a stator | |
US2642263A (en) | Blade apparatus | |
US3836282A (en) | Stator vane support and construction thereof | |
US2914300A (en) | Nozzle vane support for turbines | |
US2812159A (en) | Securing means for turbo-machine blading | |
US3554668A (en) | Turbomachine rotor | |
US3708242A (en) | Supporting structure for the blades of turbomachines | |
US2610823A (en) | Turbine bucket damping arrangement | |
EP2623723B1 (en) | Clearance control system for a gas turbine engine section | |
GB2070700A (en) | Gas turbine seals | |
JPH10503819A (en) | Vibration damping shroud for turbomachine blades | |
US1858067A (en) | Elastic fluid turbine | |
JPS58118327A (en) | Supporting structure of bearing | |
US3932056A (en) | Vane damping | |
US2489522A (en) | Brake drum cooling and silencing device | |
US3893782A (en) | Turbine blade damping | |
US3880550A (en) | Outer seal for first stage turbine | |
US2836392A (en) | Disc vibration damping means | |
US2344444A (en) | Construction of turbomachines | |
GB1437510A (en) | Compressor or turbine vane damping | |
US3773435A (en) | Flexible blade fan |