JP2014530146A - 航空機用プロペラ(単数または複数)およびプロペラのピッチを変更するシステムを備えたターボエンジン - Google Patents
航空機用プロペラ(単数または複数)およびプロペラのピッチを変更するシステムを備えたターボエンジン Download PDFInfo
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- 230000007246 mechanism Effects 0.000 claims abstract description 34
- 230000005540 biological transmission Effects 0.000 claims abstract description 21
- 238000006073 displacement reaction Methods 0.000 claims abstract description 12
- 230000008859 change Effects 0.000 claims abstract description 8
- 239000012530 fluid Substances 0.000 claims abstract description 5
- 238000011144 upstream manufacturing Methods 0.000 claims description 16
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 239000003638 chemical reducing agent Substances 0.000 description 7
- 239000007789 gas Substances 0.000 description 7
- 230000033001 locomotion Effects 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 210000003746 feather Anatomy 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
- B64C11/385—Blade pitch-changing mechanisms fluid, e.g. hydraulic comprising feathering, braking or stopping systems
-
- 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
- F01D7/00—Rotors with blades adjustable in operation; Control thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
-
- 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
- F02K3/072—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 with counter-rotating, e.g. fan rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
-
- 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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
- F01D1/26—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like traversed by the working-fluid substantially axially
-
- 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
- F05D2260/00—Function
- F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
-
- 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
Abstract
Description
−システムの前記環状アクチュエータは、前記プロペラを支持する固定ハウジング上に接合した状態で取り付けられ、およびプロペラの外側回転ハブに取り付けられた羽根に対向して前記プロペラの内側に取り付けられ、
−前記環状アクチュエータの可動部を前記プロペラの回転ハブの羽根に接続する前記リンク機構は中間伝達軸受を備え、中間伝達軸受は、片側がアクチュエータの可動部に固定され、他方側が回転ハブの羽根に機構を接続する手段と協働することで、回転駆動された機構の伝達軸受が固定アクチュエータの可動部の並進変位を回転機構の接続手段に伝達してプロペラの羽根の向きを変更し、
−前記リンク機構は、1組の連接ロッドもしくは、環状アクチュエータの周囲に配置される同様の要素を備え、片側が伝達軸受に接続され、他方側が半径方向回転シャフトに接続され、半径方向回転シャフトは、リンク機構の連接ロッドの並進変位に追従して、半径方向シャフトおよび結合羽根を回転駆動するように前記プロペラの羽根の根元部とそれぞれ一体化し、
−前記連接ロッドは、プロペラの回転円筒壁に回転可能に接続されこの円筒壁から軸方向に自由なリンク手段のリングに連接される
ことについて注目すべきである。
Claims (8)
- 少なくとも1つの航空機用プロペラを有するタービンエンジンにして、線形制御の環状流体アクチュエータ(25)と、プロペラ(9)の羽根(16)の向きを変更するために前記アクチュエータを前記プロペラの前記羽根に接続するリンク機構(26)とを備えた前記プロペラ(9)の前記羽根(16)のピッチを変更するシステム(23)を備えるタイプのタービンエンジンであって、
前記システムの前記環状アクチュエータ(25)は、前記プロペラを支持する固定ハウジング(13)上に接合した状態で取り付けられ、および前記プロペラの外側回転ハブ(40)に取り付けられた前記羽根に対向して前記プロペラの内側に取り付けられること、
前記環状アクチュエータの可動部を前記プロペラの前記回転ハブの前記羽根に接続する前記リンク機構(26)は中間伝達軸受(31)を備え、中間伝達軸受(31)は、片側が前記シリンダの前記可動部(29)に固定され、他方側が前記回転ハブの前記羽根に前記リンク機構を接続する手段(32)と協働することで、回転駆動された前記リンク機構の前記伝達軸受が前記固定アクチュエータの前記可動部の並進変位を前記回転機構の接続する手段(32)に伝達して前記プロペラの前記羽根の向きを変更すること、
前記リンク手段(32)は、前記環状アクチュエータ(25)の周囲に配置され、片側が前記伝達軸受(31)に接続され、他方側が半径方向回転シャフト(47)に接続される1組の連接ロッド(33)を備え、半径方向回転シャフト(47)は、前記リンク機構(26)の連接ロッドの並進変位に追従して、半径方向シャフトおよび結合羽根を回転駆動するように前記プロペラ(9)前記羽根(16)の根元部とそれぞれ一体化すること、および
前記連接ロッド(33)は、前記プロペラの回転円筒壁(38)に回転可能に接続されこの円筒壁から軸方向に自由な前記リンク手段(32)のリング(40)に連接されること
を特徴とする、タービンエンジン。 - 前記リンク機構(26)の前記中間伝達軸受(31)が、玉軸受もしくは同様の要素であり、前記中間伝達軸受(31)の内側リング(35)は、前記環状アクチュエータの前記可動部(29)に接合した状態で軸方向に取り付けられ、外側リング(37)は、前記アクチュエータの変位に追従するために、前記プロペラ(9)と一体化した回転円筒壁(38)に回転可能に接続されて前記壁に沿って自由に並進運動する前記機構(26)の前記リンク手段(32)と協働する、請求項1に記載のタービンエンジン。
- 前記軸受の前記玉軸受(31)が、2列の玉(34)もしくは同様の要素を備える、請求項2に記載のタービンエンジン。
- 前記連接ロッド(33)が、一方が前記リンク手段(32)の前記リング(40)に連接され、他方が前記羽根の前記回転シャフト(47)に配設された横方向ジャーナル(46)に連接される、請求項1〜請求項3のいずれか一項に記載のタービンエンジン。
- 前記伝達軸受(31)が収容される前記機構の前記リンク手段(32)の前記リング(40)と前記プロペラの前記回転円筒壁(38)との接続が、前記プロペラの軸に平行なスプライン(41、42)もしくは同様の要素を使用したタイプの接続である、請求項4に記載のタービンエンジン。
- 前記環状制御アクチュエータ(25)が、前記プロペラ(9)の前記ハブ(14)とほぼ一直線上に配置される、請求項1〜請求項5のうちのいずれか一項に記載のタービンエンジン。
- 前記環状アクチュエータ(25)の可動部(29)および固定部(27)それぞれが、2つの部分を通る前記アクチュエータに平行な少なくとも1つの軸方向ロッド(39)によって互いに回転が阻止される、請求項1〜請求項6のいずれか一項に記載のタービンエンジン。
- 上流側および下流側それぞれに二重反転するように位置合わせされた2つのプロペラを備えるタイプのタービンエンジンであって、少なくとも上流側プロペラ(9)には、請求項1〜請求項7のうちのいずれか一項に記載の前記羽根(16)のピッチを変更する前記システム(23)が配設されることを特徴とする、タービンエンジン。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1158891 | 2011-10-03 | ||
FR1158891A FR2980770B1 (fr) | 2011-10-03 | 2011-10-03 | Turbomachine a helice(s) pour aeronef avec systeme pour changer le pas de l'helice. |
PCT/FR2012/052241 WO2013050704A1 (fr) | 2011-10-03 | 2012-10-03 | Turbomachine a helice(s) pour aeronef avec systeme pour changer le pas de l'helice |
Publications (2)
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JP2014530146A true JP2014530146A (ja) | 2014-11-17 |
JP6082939B2 JP6082939B2 (ja) | 2017-02-22 |
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JP2014533968A Active JP6082939B2 (ja) | 2011-10-03 | 2012-10-03 | 航空機用プロペラ(単数または複数)およびプロペラのピッチを変更するシステムを備えたターボエンジン |
Country Status (9)
Country | Link |
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US (1) | US9849970B2 (ja) |
EP (1) | EP2763893B1 (ja) |
JP (1) | JP6082939B2 (ja) |
CN (1) | CN103874630B (ja) |
BR (1) | BR112014007972B1 (ja) |
CA (1) | CA2850702C (ja) |
FR (1) | FR2980770B1 (ja) |
RU (1) | RU2604760C2 (ja) |
WO (1) | WO2013050704A1 (ja) |
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Also Published As
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BR112014007972B1 (pt) | 2021-06-15 |
RU2604760C2 (ru) | 2016-12-10 |
FR2980770B1 (fr) | 2014-06-27 |
JP6082939B2 (ja) | 2017-02-22 |
US20140294585A1 (en) | 2014-10-02 |
FR2980770A1 (fr) | 2013-04-05 |
CN103874630B (zh) | 2016-03-30 |
CA2850702A1 (fr) | 2013-04-11 |
RU2014116249A (ru) | 2015-11-10 |
EP2763893A1 (fr) | 2014-08-13 |
CN103874630A (zh) | 2014-06-18 |
US9849970B2 (en) | 2017-12-26 |
BR112014007972A2 (pt) | 2017-04-11 |
EP2763893B1 (fr) | 2017-01-11 |
WO2013050704A1 (fr) | 2013-04-11 |
CA2850702C (fr) | 2018-11-20 |
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