JP4917302B2 - 統合された発電機を含むターボ機械 - Google Patents
統合された発電機を含むターボ機械 Download PDFInfo
- Publication number
- JP4917302B2 JP4917302B2 JP2005338178A JP2005338178A JP4917302B2 JP 4917302 B2 JP4917302 B2 JP 4917302B2 JP 2005338178 A JP2005338178 A JP 2005338178A JP 2005338178 A JP2005338178 A JP 2005338178A JP 4917302 B2 JP4917302 B2 JP 4917302B2
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- Prior art keywords
- generator
- turbomachine
- rotor
- compressor
- cooling circuit
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- 238000001816 cooling Methods 0.000 claims description 24
- 238000011144 upstream manufacturing Methods 0.000 claims description 11
- 238000002485 combustion reaction Methods 0.000 claims description 10
- 239000007858 starting material Substances 0.000 claims description 9
- 230000006835 compression Effects 0.000 claims description 7
- 238000007906 compression Methods 0.000 claims description 7
- 238000005461 lubrication Methods 0.000 claims description 6
- 230000002093 peripheral effect Effects 0.000 claims description 6
- 230000001050 lubricating effect Effects 0.000 claims description 5
- 239000010687 lubricating oil Substances 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 2
- 239000003921 oil Substances 0.000 description 23
- 239000003595 mist Substances 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
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
- F01D25/18—Lubricating 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
-
- 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
- F02K3/06—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 front fan
-
- 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
- F05D2220/70—Application in combination with
- F05D2220/76—Application in combination with an electrical generator
-
- 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
- F05D2260/85—Starting
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Motor Or Generator Cooling System (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
・ 発電機60を収容するボックスは、それ自体が密封されており、このボックスは、円筒形支持体41、45によって形成される。より正確には、ステータ64とロータ62との間のこの密封は、好適にはカーボンで作られた2個のブラシガスケット68によって達成される。これらのガスケット68は、ステータ64の前端部と後端部とに(より正確には、円筒形支持体45の前端部45aと後端部45bの自由縁部に)取り付けられ、これらのガスケットは、ロータ62のための円筒形支持体41の前端部と後端部とに押し付けられる(この構成は、逆も可能である)。
・ 発電機60を収容するボックス内の(円筒形支持体41と円筒形支持体45とによって画定される)空間は、円筒形支持体45の壁内に開いている補助空気供給ダクト70によって加圧される。
12 周辺カウル
14 ファン
15、62 ロータ
16 低圧圧縮機
17 中間ケーシング
18 高圧圧縮機
20 燃焼チャンバ
22 高圧タービン
24 低圧タービン
26 低圧シャフト
28 前部軸受け
30 中間軸受け
32 チューブ
34 前部シュラウド
36 中間シュラウド
38 高圧シャフト
40 円筒形シュラウド
41、45 円筒形支持体
42 後部軸受け
44 支持構造体
46 エンクロージャ
48、50、52、76 ノズル
60 発電機
64 ステータ
66 接続部
68 ブラシガスケット
72、78 らせん状チャネル
74 油供給部
80、82 開口部
Claims (11)
- 高圧スプールと、ロータ(38)に取り付けられ、かつケーシングを含む軸方向の高圧圧縮機(18)と、前記圧縮機(18)の前部であって前記圧縮機(18)のケーシングとロータ(38)との間に配置された少なくとも一つの後部軸受け(42)とを含む、ターボ機械であって、前記ターボ機械が、前記スプールと同軸の発電機(60)をさらに含み、該発電機(60)が、圧縮機(18)の前記ロータ(38)と共に回転するように拘束された1次磁気回路(62)と、前記ケーシングに固定された2次磁気回路(64)とを含み、
前記発電機(60)が、前記後部軸受け(42)から上流側に配置されることと、前記発電機(60)が、第1の冷却回路(72)を少なくとも含み、該第1の冷却回路(72)が、前記2次磁気回路(64)を取り囲み、かつ前記後部軸受け(42)を潤滑するためのノズル(52)によって延長されることとを特徴とする、ターボ機械。 - 前記ターボ機械が、燃焼チャンバ(20)をさらに含むことと、前記燃焼チャンバ(20)から上流側で、前記スプールが、前記燃焼チャンバに空気を送るための前記軸方向の高圧圧縮機(18)を呈し、前記燃焼チャンバから下流側で、前記スプールが、回転時に、前記圧縮機(18)のロータ(38)を駆動するための前記燃焼チャンバ(20)からの高温ガスを受けるためのタービン(22)を呈し、前記圧縮機が、複数の圧縮段を含んでおり、各圧縮段が、前記ケーシングに固定された静止ブレードのリングと、前記ロータの円板の周縁部から径方向に延びる可動ブレードのリングとを呈することとを特徴とする、請求項1に記載のターボ機械。
- 前記ターボ機械が、前記高圧スプールから上流側に配置される低圧圧縮機(16)を有する低圧スプールと、前記高圧スプールから下流側に配置されて、回転時に前記低圧圧縮機のロータ(15)を駆動するために役立つ低圧タービン(24)とをさらに含み、前記圧縮機が、複数の圧縮段を含み、各圧縮段が、静止ブレードのリングと、前記ロータの各円板の周縁部から径方向に延びる可動ブレードのリングとを呈し、前記ターボ機械が、低圧圧縮機(16)と高圧圧縮機(18)との間に配置された中間ケーシング(17)をさらに含むことと、前記発電機の2次磁気回路(64)が、前記中間ケーシング(17)に固定されることと、前記後部軸受け(42)が、前記中間ケーシング(17)に取り付けられることとを特徴とする、請求項1または2に記載のターボ機械。
- 前記発電機(60)が、スタータとして動作するように構成されることを特徴とする、請求項1、2、または3に記載のターボ機械。
- 前記発電機(60)が、補助発電機として動作するように構成されることを特徴とする、請求項1から4のいずれか一項に記載のターボ機械。
- 前記ターボ機械が、前記発電機(60)から上流側で、前記中間ケーシング(17)と前記低圧圧縮機のロータ(15)との間に配置された少なくとも一つの前部軸受け(28、30)をさらに含むことと、前記第1の冷却回路(72)が、前記前部軸受け(28、30)の潤滑油回路と連通していることとを特徴とする、請求項3に記載のターボ機械。
- 前記ターボ機械が、前記1次磁気回路(62)に取り囲まれ、かつ第1の冷却回路(72)に接続された供給手段(76)によって供給される第2の冷却回路(78)をさらに含み、前記第2の冷却回路(78)が、前記前部軸受け(28、30)の近傍で開いていることを特徴とする、請求項6に記載のターボ機械。
- 前記第2の冷却回路(78)の前記供給手段(76)が、後部軸受け(42)を潤滑するための前記ノズル(52)と共に2ヘッドノズルを構成する、潤滑ノズルを含むことを特徴とする、請求項7に記載のターボ機械。
- 前記2次磁気回路(64)が、円筒形支持体(45)に取り付けられることと、前記1次磁気回路(62)が、円筒形支持体(41)に取り付けられることと、環状の密封手段(68)が、前記円筒形支持体(41、45)の端部間に配置され、それによって、前記発電機(60)に発電機(60)を取り巻く潤滑油雰囲気に対する耐性を与えていることとを特徴とする、請求項1から8のいずれか一項に記載のターボ機械。
- 前記第1の冷却回路(72)が、第1の一連のらせん状チャネルを含むことを特徴とする、請求項1から9のいずれか一項に記載のターボ機械。
- 前記第2の冷却回路(78)が、第2の一連のらせん状チャネルを含むことを特徴とする、請求項7に記載のターボ機械。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0412504A FR2878286B1 (fr) | 2004-11-25 | 2004-11-25 | Turbomachine comportant un generateur de courant electrique integre |
FR0412504 | 2004-11-25 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2006153012A JP2006153012A (ja) | 2006-06-15 |
JP4917302B2 true JP4917302B2 (ja) | 2012-04-18 |
Family
ID=34951287
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005338178A Active JP4917302B2 (ja) | 2004-11-25 | 2005-11-24 | 統合された発電機を含むターボ機械 |
Country Status (5)
Country | Link |
---|---|
US (1) | US7224082B2 (ja) |
EP (1) | EP1662636B1 (ja) |
JP (1) | JP4917302B2 (ja) |
FR (1) | FR2878286B1 (ja) |
RU (1) | RU2424435C2 (ja) |
Families Citing this family (39)
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FR2896537B1 (fr) * | 2006-01-24 | 2011-07-29 | Snecma | Turbomachine a generateur-demarreur integre |
GB2443194B (en) * | 2006-10-24 | 2008-09-10 | Rolls-Royce Plc | Gas turbine engine |
US7832193B2 (en) * | 2006-10-27 | 2010-11-16 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7468561B2 (en) * | 2007-03-27 | 2008-12-23 | General Electric Company | Integrated electrical power extraction for aircraft engines |
FR2915523A1 (fr) * | 2007-04-27 | 2008-10-31 | Snecma Sa | Dispositif de production d'energie electrique dans un moteur a turbine a gaz a double corps |
US7854582B2 (en) * | 2007-05-08 | 2010-12-21 | Pratt & Whitney Canada Corp. | Operation of an aircraft engine after emergency shutdown |
US7926287B2 (en) * | 2007-05-08 | 2011-04-19 | Pratt & Whitney Canada Corp. | Method of operating a gas turbine engine |
FR2919896B1 (fr) | 2007-08-07 | 2009-10-30 | Snecma Sa | Turboreacteur comprenant un generateur de courant monte dans la soufflante et un procede de montage dudit generateur dans la soufflante |
US8438859B2 (en) * | 2008-01-08 | 2013-05-14 | Rolls-Royce North American Technologies, Inc. | Integrated bypass engine structure |
US8039983B2 (en) * | 2008-12-02 | 2011-10-18 | The Boeing Company | Systems and methods for providing AC power from multiple turbine engine spools |
US8278774B2 (en) | 2009-06-29 | 2012-10-02 | Pratt & Whitney Canada Corp. | Gas turbine with wired shaft forming part of a generator/motor assembly |
US8097972B2 (en) * | 2009-06-29 | 2012-01-17 | Pratt & Whitney Canada Corp. | Gas turbine with magnetic shaft forming part of a generator/motor assembly |
US20110018273A1 (en) * | 2009-07-27 | 2011-01-27 | Rolls-Royce Corporation | Starter/generator integrated into compressor of turbine engine |
DE102010014968A1 (de) | 2010-04-14 | 2011-10-20 | Mtu Aero Engines Gmbh | Mehrwelliges Triebwerk mit Tandem-Generator |
DE102010049885B4 (de) * | 2010-11-01 | 2015-06-25 | Rolls-Royce Deutschland Ltd & Co Kg | Strahltriebwerk |
US8723349B2 (en) | 2011-10-07 | 2014-05-13 | General Electric Company | Apparatus for generating power from a turbine engine |
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FR2989734B1 (fr) * | 2012-04-24 | 2014-04-18 | Snecma | Turboreacteur incorporant des generateurs thermoelectriques |
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US9874110B2 (en) | 2013-03-07 | 2018-01-23 | Rolls-Royce North American Technologies Inc. | Cooled gas turbine engine component |
FR3011277B1 (fr) * | 2013-09-30 | 2018-04-06 | Turbomeca | Turbomachine adaptee a fonctionner en mode vireur |
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EP3080424B1 (en) * | 2013-12-13 | 2022-05-04 | Raytheon Technologies Corporation | Architecture for an axially compact, high performance propulsion system |
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US10557372B2 (en) * | 2015-12-17 | 2020-02-11 | General Electric Company | Systems and methods for assessing strain of components in turbomachines |
US20170298830A1 (en) * | 2016-04-18 | 2017-10-19 | General Electric Company | Oil-free gas turbine engine |
US10308366B2 (en) * | 2016-08-22 | 2019-06-04 | General Electric Company | Embedded electric machine |
US11067003B2 (en) * | 2017-09-29 | 2021-07-20 | General Electric Company | Fluid cooling structure for an electric machine of a gas turbine engine |
FR3080650B1 (fr) * | 2018-04-26 | 2020-04-03 | Safran Aircraft Engines | Ensemble de lubrification pour une turbomachine |
FR3087819B1 (fr) * | 2018-10-26 | 2020-11-13 | Safran Aircraft Engines | Turbomachine d'aeronef equipee d'une machine electrique |
FR3087820B1 (fr) * | 2018-10-26 | 2020-10-16 | Safran Aircraft Engines | Turbomachine d'aeronef equipee d'une machine electrique |
US20200325821A1 (en) | 2019-04-09 | 2020-10-15 | Rolls-Royce North American Technologies Inc. | Starter/generator |
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RU2767579C2 (ru) * | 2020-01-29 | 2022-03-17 | Никита Александрович Королев | Турбогенератор |
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GB2613076B (en) | 2021-10-15 | 2024-06-05 | Rtx Corp | Electric machine within a turbine engine |
FR3134428A1 (fr) * | 2022-04-11 | 2023-10-13 | Safran Aircraft Engines | Système de lubrification commun à deux enceintes d’une turbomachine |
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-
2004
- 2004-11-25 FR FR0412504A patent/FR2878286B1/fr not_active Expired - Fee Related
-
2005
- 2005-11-21 EP EP05292462.8A patent/EP1662636B1/fr active Active
- 2005-11-21 US US11/282,669 patent/US7224082B2/en active Active
- 2005-11-24 JP JP2005338178A patent/JP4917302B2/ja active Active
- 2005-11-24 RU RU2005136640/06A patent/RU2424435C2/ru active
Also Published As
Publication number | Publication date |
---|---|
EP1662636A2 (fr) | 2006-05-31 |
FR2878286A1 (fr) | 2006-05-26 |
US20060108807A1 (en) | 2006-05-25 |
RU2424435C2 (ru) | 2011-07-20 |
EP1662636A3 (fr) | 2012-05-30 |
FR2878286B1 (fr) | 2009-05-22 |
US7224082B2 (en) | 2007-05-29 |
RU2005136640A (ru) | 2007-05-27 |
EP1662636B1 (fr) | 2013-11-06 |
JP2006153012A (ja) | 2006-06-15 |
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