WO2015041083A1 - ターボファンエンジンのためのシール - Google Patents
ターボファンエンジンのためのシール Download PDFInfo
- Publication number
- WO2015041083A1 WO2015041083A1 PCT/JP2014/073643 JP2014073643W WO2015041083A1 WO 2015041083 A1 WO2015041083 A1 WO 2015041083A1 JP 2014073643 W JP2014073643 W JP 2014073643W WO 2015041083 A1 WO2015041083 A1 WO 2015041083A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- seal
- vane
- liner
- rib portion
- fillet
- Prior art date
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
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
-
- 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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/29—Three-dimensional machined; miscellaneous
- F05D2250/292—Three-dimensional machined; miscellaneous tapered
-
- 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
- F05D2300/40—Organic materials
- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
- F05D2300/431—Rubber
-
- 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
Definitions
- the present invention relates to a seal for a turbofan engine, and more particularly to a seal for sealing a gap between a vane and a liner in an outlet guide vane.
- the turbofan engine is a jet engine having a bypass duct around the core engine.
- the fan is driven using a part of the energy generated by the engine, and a part of the air flow generated by the fan is compressed by the compressor and used for combustion of the engine, while the other part is passed through the bypass duct. And erupt directly backward.
- the air flow through the bypass duct itself generates thrust to contribute to increased engine thrust and improve engine energy efficiency.
- ⁇ Exit guide vanes are provided in the bypass duct.
- the outlet guide vanes are a plurality of vanes extending in the radial direction, and the vanes are arranged in the circumferential direction to form an annular structure.
- the air flow generated by the fan is a vortex-like flow that rotates around its axis, but is rectified by passing through the outlet guide vanes and goes straight backward. Since the outlet guide vane may also have a function of connecting and supporting the fan case surrounding the bypass duct and the core portion, the outlet guide vane needs to have sufficient strength and rigidity.
- the seal is required to smoothly connect the vane surface and the liner surface. It is difficult to form such a seal by automatic work. For example, it requires time-consuming work, such as placing paste-like sealing material on the relevant part by hand and finishing it after solidifying. It is.
- the present invention has been made in view of the above-described problems, and it is an object of the present invention to provide a seal capable of sealing an airflow simply by assembling an outlet guide vane together with a liner and a vane attached to the liner.
- the seal for sealing the gap between the vane and the liner in the outlet guide vane has a shape that gradually decreases toward the tip to form a rounded corner in contact with the vane.
- a rib portion is a shape that gradually decreases toward the tip to form a rounded corner in contact with the vane.
- the rib portion has one shape selected from the group consisting of a cylinder, an elliptic cylinder, a prism, and a fillet shape that gradually becomes thinner toward the tip.
- the rib portion is hollow to facilitate crushing. More preferably, the fillet part and the rib part are integrally formed.
- a seal that can seal the airflow and can form a rounded corner that does not disturb the airflow simply by assembling the outlet guide vane to the liner is provided.
- FIG. 1 is a schematic longitudinal sectional view of a turbofan engine.
- FIG. 2 is a perspective view of an outlet guide vane incorporating a seal according to one embodiment.
- FIG. 3A is a partial cross-sectional view of the outlet guide vane, particularly showing the relationship between the seal and the structure for fixing the vane.
- FIG. 3B is a partial cross-sectional view of the outlet guide vane showing the seal particularly enlarged.
- FIG. 4 is a cross-sectional view of the seal shown with a portion of the liner.
- FIG. 5 is a cross-sectional view of a seal according to a modification.
- FIG. 6 is a cross-sectional view of a seal according to another modification.
- FIG. 7 is a cross-sectional view of a seal according to still another modification.
- the turbofan engine 1 includes a fan 3 at its center, and a bypass duct is secured between the inner wall of the nacelle 5 surrounding the periphery and the core portion 7. Part a of the air flow generated by the fan 3 flows into the low-pressure compressor 9 and is used for engine combustion, while the other part b flows into the bypass duct. A part b of the air flow passing through the bypass duct is rectified by an outlet guide vane composed of a plurality of vanes 11 and ejected rearward.
- each vane 11 is a plate-like structure extending in the radial direction having an airfoil shape for rectification.
- the outer end is sandwiched between the fixing structures 13, and the inner end is sandwiched between the similar structures 15, thereby being fixed to the nacelle 5 and the core portion 7.
- the outer liner 17 is disposed adjacent to the structure 13 for fixing the outer end so that the edge thereof is in contact with the surface of the vane 11.
- the inner liner 19 is disposed adjacent to the structure 15 for fixing the inner end so that the edge thereof is in contact with the surface of the vane 11.
- a combination of the vane 11 and the liners 17 and 19 is arranged in the circumferential direction in contact with each other, thereby forming an annular structure.
- the plurality of outer liners 17 arranged in a cylindrical shape form a part of the inner wall
- the plurality of inner liners 19 arranged in a cylindrical shape also form a part of the outer wall of the core portion, and the outer liner 17 and the inner liner 19 are Enclose the bypass duct.
- the seal 21 is used to seal a gap between the inner liner 19 and the vane 11, for example.
- it may be applied to the gap between the outer liner 17 and the vane 11 or may be used for the purpose of sealing any other gap.
- an example applied to the inner liner 19 will be described, but the present invention is not limited to this.
- the inner end 11e of the vane 11 is sandwiched by the structure 15 for fixing the inner end, but the structure 15 has a flat upper surface directly above the inner end 11e.
- the seal 21 is used by being coupled to one end of the inner liner 19.
- the seal 21 includes a coupling portion 23, and the coupling portion 23 can have an appropriate structure suitable for coupling with the inner liner 19.
- Such a structure may be, for example, an appropriate unevenness for engagement as shown in the figure, or any other structure that increases the contact surface.
- the increased contact surface is advantageous for bonding the seal 21 and the inner liner 19.
- the seal 21 has a fillet portion 27 in the vicinity of its proximal end, for example, which is about the same thickness as the inner liner 19, but gradually becomes thinner toward the distal end.
- the seal 21 may be flexible at least at the fillet portion 27, or may be entirely flexible.
- An elastomer such as synthetic rubber can be applied to the seal 21 to provide flexibility.
- the fillet portion 27 warps upward when contacting the vane 11, thereby forming a rounded corner between the inner liner 19 and the vane 11.
- the fillet portion 27 may have a shape that warps upward in advance as illustrated.
- the seal 21 further has a rib portion 25 protruding from the inner surface thereof.
- the rib portion 25 is a protrusion extending substantially along the entire length of the seal 21 in the longitudinal direction.
- the rib portion 25 is also flexible, and when it comes into contact with the upper surface of the structure 15 that fixes the vane 11, the rib portion 25 is crushed and brought into close contact therewith. Accordingly, the rib portion 25 is kept airtight with the upper surface of the structure 15.
- the rib portion 25 has an appropriate position and size selected according to the position of the upper surface of the structure 15 and according to the distance from the seal 21 to the upper surface of the structure 15.
- the rib portion 25 and the fillet portion 27 are preferably integrated as shown in FIG. However, like the seal 21 ′ shown in FIG. 5, the rib portion 25 t and the fillet portion 27 f may be separate. In that case, the rib portion 25t is directly coupled to the inner liner 19 '.
- a hollow cylindrical shape having a hole 25h inside can be selected to facilitate crushing, but a solid rib portion 25s may be used as shown in FIG. .
- other appropriate shapes such as an elliptic cylinder and a prism can be selected.
- a fillet shape that gradually decreases toward the tip can be applied to the rib portion 25f.
- the rib portion 25f may be appropriately warped to generate a force for pressing the fillet portion 27 toward the vane 11 when contacting the structure 15.
- the seal 21 is used for assembly in a state of being coupled to the inner liner 19.
- the fillet portion 27 at the tip thereof is in contact with the surface of the vane 11 and warps upward to form a round corner that does not disturb the air flow. Since the vane 11 is a curved surface, it is difficult for any structure to make airtight contact with the entire surface, and the fillet portion 27 according to the present embodiment is no exception. However, since the rib portion 25f is in contact with the upper surface of the structure 15 and remains airtight instead of the fillet portion 27, the seal 21 can seal the air flow in the bypass duct.
- the seal according to the present embodiment can seal the air flow only by assembling the outlet guide vane and attaching it to the liner without requiring laborious work, and does not disturb the air flow.
- a seal that can seal the airflow simply by assembling the outlet guide vane together with the liner and vane after being attached to the liner is provided.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims (4)
- 出口案内翼においてベーンとライナとの間の隙間を封ずるためのシールであって、
前記ライナと結合する結合部と、
前記結合部から延び、前記ベーンに接して前記ベーンと前記ライナとの間の丸い隅を構成するべく、先端に向かって次第に薄くなる形状を有する可撓性のフィレット部と、
内面から突出した可撓性のリブ部であって、前記ベーンを固定するための外部構造の上面に接して気密を保つべく寸法づけられたリブ部と、
を備えたシール。 - 請求項1のシールであって、前記リブ部は、円柱、楕円円柱、角柱、先端に向かって次第に薄くなるフィレット形状、よりなる群より選択された一の形状を有する、シール。
- 請求項1のシールであって、前記リブ部は押し潰しを容易にするべく中空である、シール。
- 請求項1乃至3の何れか1項のシールであって、前記フィレット部と前記リブ部とは一体に形成されている、シール。
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201480050715.6A CN105531445B (zh) | 2013-09-18 | 2014-09-08 | 用于涡轮风扇发动机的密封件 |
RU2016114283A RU2641421C2 (ru) | 2013-09-18 | 2014-09-08 | Уплотнение для турбовентиляторного двигателя |
CA2924425A CA2924425C (en) | 2013-09-18 | 2014-09-08 | Seal for turbofan engine |
EP14845489.5A EP3048260B1 (en) | 2013-09-18 | 2014-09-08 | Seal for turbofan engine |
US15/068,750 US10233765B2 (en) | 2013-09-18 | 2016-03-14 | Seal for turbofan engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2013192710A JP6221544B2 (ja) | 2013-09-18 | 2013-09-18 | ターボファンエンジンのためのシール |
JP2013-192710 | 2013-09-18 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/068,750 Continuation US10233765B2 (en) | 2013-09-18 | 2016-03-14 | Seal for turbofan engine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015041083A1 true WO2015041083A1 (ja) | 2015-03-26 |
Family
ID=52688734
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2014/073643 WO2015041083A1 (ja) | 2013-09-18 | 2014-09-08 | ターボファンエンジンのためのシール |
Country Status (7)
Country | Link |
---|---|
US (1) | US10233765B2 (ja) |
EP (1) | EP3048260B1 (ja) |
JP (1) | JP6221544B2 (ja) |
CN (1) | CN105531445B (ja) |
CA (1) | CA2924425C (ja) |
RU (1) | RU2641421C2 (ja) |
WO (1) | WO2015041083A1 (ja) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11035238B2 (en) * | 2012-06-19 | 2021-06-15 | Raytheon Technologies Corporation | Airfoil including adhesively bonded shroud |
FR3048719B1 (fr) * | 2016-03-14 | 2018-03-02 | Safran Aircraft Engines | Redresseur de flux pour turbomachine avec plateformes integrees et rapportees |
FR3087831B1 (fr) * | 2018-10-30 | 2022-06-24 | Safran Aircraft Engines | Aube comprenant une structure en materiau composite et une piece de raidissement metallique |
FR3089270B1 (fr) * | 2018-11-29 | 2020-11-13 | Safran Aircraft Engines | Joint d’etanchéité pour porte de vanne de décharge d’une turbomachine |
GB201904727D0 (en) | 2019-04-04 | 2019-05-22 | Rolls Royce Plc | Seal assembly |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH10325303A (ja) | 1997-04-24 | 1998-12-08 | United Technol Corp <Utc> | ファンブレードインタープラットフォームシール |
JP2009508033A (ja) * | 2005-09-12 | 2009-02-26 | プラット アンド ホイットニー カナダ コーポレイション | アウタグロメットを有するベーンアッセンブリ |
US20110037233A1 (en) * | 2009-08-14 | 2011-02-17 | Rolls-Royce Plc | Sealing assembly |
JP2011085055A (ja) * | 2009-10-15 | 2011-04-28 | General Electric Co <Ge> | フェアリングシール |
JP2012511661A (ja) | 2008-12-12 | 2012-05-24 | スネクマ | タービンエンジンのロータ内のプラットフォームのためのシール |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2599081B1 (fr) * | 1986-05-23 | 1988-07-29 | Snecma | Redresseur de soufflante de turboreacteur multiflux |
FR2600379B1 (fr) * | 1986-06-18 | 1988-09-02 | Snecma | Redresseur de soufflante de turboreacteur multiflux |
FR2610673B1 (fr) * | 1987-02-05 | 1991-03-15 | Snecma | Turboreacteur multiflux a couronne externe de redresseur de soufflante frettee sur le carter |
GB9602129D0 (en) * | 1996-02-02 | 1996-04-03 | Rolls Royce Plc | Rotors for gas turbine engines |
US6290459B1 (en) | 1999-11-01 | 2001-09-18 | General Electric Company | Stationary flowpath components for gas turbine engines |
US7628578B2 (en) | 2005-09-12 | 2009-12-08 | Pratt & Whitney Canada Corp. | Vane assembly with improved vane roots |
GB0806171D0 (en) * | 2008-04-07 | 2008-05-14 | Rolls Royce Plc | Aeroengine fan assembly |
US20100077612A1 (en) * | 2008-09-30 | 2010-04-01 | Courtney James Tudor | Method of manufacturing a fairing with an integrated seal |
GB0910752D0 (en) * | 2009-06-23 | 2009-08-05 | Rolls Royce Plc | An annulus filler for a gas turbine engine |
JP2011085056A (ja) * | 2009-10-15 | 2011-04-28 | General Electric Co <Ge> | 一体形シールを有するフェアリングシールを製作する方法 |
GB2490858B (en) * | 2011-03-22 | 2014-01-01 | Rolls Royce Plc | A bladed rotor |
-
2013
- 2013-09-18 JP JP2013192710A patent/JP6221544B2/ja active Active
-
2014
- 2014-09-08 RU RU2016114283A patent/RU2641421C2/ru active
- 2014-09-08 CA CA2924425A patent/CA2924425C/en active Active
- 2014-09-08 EP EP14845489.5A patent/EP3048260B1/en active Active
- 2014-09-08 CN CN201480050715.6A patent/CN105531445B/zh active Active
- 2014-09-08 WO PCT/JP2014/073643 patent/WO2015041083A1/ja active Application Filing
-
2016
- 2016-03-14 US US15/068,750 patent/US10233765B2/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH10325303A (ja) | 1997-04-24 | 1998-12-08 | United Technol Corp <Utc> | ファンブレードインタープラットフォームシール |
JP2009508033A (ja) * | 2005-09-12 | 2009-02-26 | プラット アンド ホイットニー カナダ コーポレイション | アウタグロメットを有するベーンアッセンブリ |
JP2012511661A (ja) | 2008-12-12 | 2012-05-24 | スネクマ | タービンエンジンのロータ内のプラットフォームのためのシール |
US20110037233A1 (en) * | 2009-08-14 | 2011-02-17 | Rolls-Royce Plc | Sealing assembly |
JP2011085055A (ja) * | 2009-10-15 | 2011-04-28 | General Electric Co <Ge> | フェアリングシール |
Non-Patent Citations (1)
Title |
---|
See also references of EP3048260A4 * |
Also Published As
Publication number | Publication date |
---|---|
JP6221544B2 (ja) | 2017-11-01 |
CA2924425C (en) | 2017-06-06 |
CN105531445B (zh) | 2017-05-17 |
RU2016114283A (ru) | 2017-10-23 |
EP3048260A4 (en) | 2017-04-19 |
JP2015059459A (ja) | 2015-03-30 |
CN105531445A (zh) | 2016-04-27 |
EP3048260B1 (en) | 2020-11-11 |
US20160194971A1 (en) | 2016-07-07 |
US10233765B2 (en) | 2019-03-19 |
EP3048260A1 (en) | 2016-07-27 |
CA2924425A1 (en) | 2015-03-26 |
RU2641421C2 (ru) | 2018-01-17 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2015041083A1 (ja) | ターボファンエンジンのためのシール | |
JP4098395B2 (ja) | ファンブレードインタープラットフォームシール | |
CN106894845B (zh) | 用于多壁叶片的冷却回路 | |
CN106894844B (zh) | 用于多壁叶片的冷却回路 | |
JP5962942B2 (ja) | 複合材翼 | |
US8075255B2 (en) | Reducing inter-seal gap in gas turbine | |
CN107035417B (zh) | 用于多壁叶片的冷却回路 | |
US10408066B2 (en) | Suction side turbine blade tip cooling | |
US8690536B2 (en) | Turbine blade tip with vortex generators | |
US20100326048A1 (en) | Gas turbine engine duct having a coupled fluid volume | |
US8051662B2 (en) | Transition duct assemblies and gas turbine engine systems involving such assemblies | |
JP6461382B2 (ja) | シュラウド付きタービンブレード | |
EP1443215A3 (en) | Integral tip seal in a fan-shroud structure | |
US10273881B2 (en) | Foreign object damage screen for gas turbine system | |
US20120294739A1 (en) | Impeller, electric air blower using same, and electric cleaner using electric air blower | |
US9175573B2 (en) | Dovetail attachment seal for a turbomachine | |
JP6295252B2 (ja) | バイパス流れが増加したヘリコプタエンジン空気取入口 | |
US20160230580A1 (en) | Recirculation seal for use in a gas turbine engine | |
US9115591B2 (en) | Universal seal | |
EP3712381A1 (en) | Inner shroud assembly for stator vanes | |
US20130081397A1 (en) | Forward casing with a circumferential sloped surface and a combustor assembly including same | |
US10451082B2 (en) | Anti-rotation feature for wear liners | |
WO2016148691A1 (en) | Shrouded turbine airfoil with knife edge seal |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 201480050715.6 Country of ref document: CN |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 14845489 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 2924425 Country of ref document: CA |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
REEP | Request for entry into the european phase |
Ref document number: 2014845489 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2014845489 Country of ref document: EP |
|
ENP | Entry into the national phase |
Ref document number: 2016114283 Country of ref document: RU Kind code of ref document: A |