JP4860963B2 - 二重反転タービンエンジン及びそれを組立てる方法 - Google Patents
二重反転タービンエンジン及びそれを組立てる方法 Download PDFInfo
- Publication number
- JP4860963B2 JP4860963B2 JP2005245339A JP2005245339A JP4860963B2 JP 4860963 B2 JP4860963 B2 JP 4860963B2 JP 2005245339 A JP2005245339 A JP 2005245339A JP 2005245339 A JP2005245339 A JP 2005245339A JP 4860963 B2 JP4860963 B2 JP 4860963B2
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- turbine engine
- shaft
- fan
- bearing
- 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 - Fee Related
Links
- 238000000034 method Methods 0.000 title description 5
- 230000000712 assembly Effects 0.000 claims description 22
- 238000000429 assembly Methods 0.000 claims description 22
- 238000005461 lubrication Methods 0.000 claims description 22
- 239000010687 lubricating oil Substances 0.000 claims description 21
- 230000001050 lubricating effect Effects 0.000 claims description 9
- 239000000314 lubricant Substances 0.000 claims description 8
- 239000012530 fluid Substances 0.000 claims description 6
- 238000009423 ventilation Methods 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 40
- 238000005096 rolling process Methods 0.000 description 6
- 239000000567 combustion gas Substances 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 239000000284 extract Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/06—Lubrication
- F04D29/063—Lubrication specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
- F04D19/02—Multi-stage pumps
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/20—Lubricating arrangements using lubrication pumps
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/06—Lubrication
-
- 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
- F05D2250/23—Three-dimensional prismatic
- F05D2250/232—Three-dimensional prismatic conical
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Rolling Contact Bearings (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
12、14 ファン組立体
20、22 ファンシャフト
34 二重反転低圧タービン
36 外側ケーシング
38、42 タービンロータ
50、52、54、56 ファン軸受組立体
80 サンプ与圧システム
82 サンプ通気システム
88 ファンフレーム支柱
98、100 構造部材
110、112 サンプ通気空洞
114 回転コーン部
130、132 ラビリンスシール
150 軸受潤滑システム
152 軸受潤滑ドレンシステム
160 供給マニホルド
Claims (7)
- ガスタービンエンジン(10)であって、
第1の回転方向に回転するように構成された第1のファン組立体(12)と、
前記第1の回転方向とは逆の第2の回転方向に回転するように構成された第2のファン組立体(14)と、
前記第2のファン組立体の少なくとも一部分を通して潤滑流体を流すように構成された潤滑システム(150)と、
前記第1のファン組立体(12)に回転可能に結合された第1の軸受組立体(50)と、
前記第2のファン組立体(14)に回転可能に結合された第2の軸受組立体(52)と、
を含み、
前記潤滑システム(150)が、前記第1及び第2の軸受組立体に前記潤滑流体を流すように構成されており、
前記ガスタービンエンジン(10)が、前記第2のファン組立体(14)の少なくとも一部分を通して空気を流して前記第1及び第2の軸受組立体(50、52)を加圧するのを可能にするように構成されたサンプ与圧システム(80)をさらに含み、
前記第2のシャフト(22)が、該シャフトを貫通する第1の開口(94)と該シャフトを貫通する第2の開口(96)とを含み、潤滑油が、前記第1の軸受組立体(50)から前記第1の開口を通って流れかつ潤滑油が、前記第2の軸受組立体(52)から前記第2の開口を通って油だめに流れるようになっている
ことを特徴とする、ガスタービンエンジン(10)。 - 前記第1のファン組立体(12)と第1の回転方向に回転するように構成された第1のタービンロータ(38)とに結合された第1のシャフト(20)と、
前記第2のファン組立体(14)と前記第1の回転方向とは逆の第2の回転方向に回転するように構成された第2のタービンロータ(42)とに結合された第2のシャフト(22)と、
前記第2のシャフトに結合されかつ該第2のシャフトと共に回転するように構成されたコーン部(114)と、
をさらに含む、請求項1記載のガスタービンエンジン(10)。 - 潤滑マニホルド(160)と、
前記マニホルドに結合された複数の噴出口(162)と、
前記マニホルドに結合されかつ前記複数の噴出口を通して潤滑油を流して前記第1及び第2の軸受組立体(50、52)を潤滑するのを可能にするように構成されたポンプと、
をさらに含む、請求項1記載のガスタービンエンジン(10)。 - 前記コーン部(114)と前記第1のシャフト(20)との間に形成された空洞(116)をさらに含み、ポンプが、前記空洞を通して潤滑油を前記第1の軸受組立体(50)に流すようになっている、請求項1記載のガスタービンエンジン(10)。
- 前記サンプ与圧システム(80)が、
ガスタービンエンジン圧縮機出口(26)に結合されかつ少なくとも1つのファンフレーム支柱(88)を貫通する供給マニホルド(83)と、
前記供給マニホルドに結合されかつ前記第1及び前記第2の軸受組立体(50、52)に対して空気を流すように構成された第2のマニホルド(86)と、を含む、
請求項1記載のガスタービンエンジン(10)。 - 前記第2のファン組立体(14)の少なくとも一部分を通して空気を流して前記第1及び第2の軸受組立体(50、52)を通気するのを可能にするように構成されたサンプ通気システム(82)をさらに含む、請求項1記載のガスタービンエンジン(10)。
- 前記コーン部(114)が、該コーン部を貫通する第1の開口(118)を含み、かつ前記第1のシャフト(20)が、該シャフトを貫通する少なくとも1つの開口(120)を含み、空気が、前記コーン部の第1の開口を通ってかつ前記第1のシャフトの少なくとも1つの開口を通って前記第1のシャフト内に流れるようになっている、請求項6記載のガスタービンエンジン(10)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/976,523 | 2004-10-29 | ||
US10/976,523 US7458202B2 (en) | 2004-10-29 | 2004-10-29 | Lubrication system for a counter-rotating turbine engine and method of assembling same |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2006125386A JP2006125386A (ja) | 2006-05-18 |
JP2006125386A5 JP2006125386A5 (ja) | 2008-10-09 |
JP4860963B2 true JP4860963B2 (ja) | 2012-01-25 |
Family
ID=34976516
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005245339A Expired - Fee Related JP4860963B2 (ja) | 2004-10-29 | 2005-08-26 | 二重反転タービンエンジン及びそれを組立てる方法 |
Country Status (5)
Country | Link |
---|---|
US (1) | US7458202B2 (ja) |
JP (1) | JP4860963B2 (ja) |
CA (1) | CA2516752C (ja) |
FR (1) | FR2877407B1 (ja) |
GB (1) | GB2419639B (ja) |
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US7694505B2 (en) * | 2006-07-31 | 2010-04-13 | General Electric Company | Gas turbine engine assembly and method of assembling same |
FR2918120B1 (fr) * | 2007-06-28 | 2009-10-02 | Snecma Sa | Turbomachine a double soufflante |
FR2927366B1 (fr) * | 2008-02-13 | 2013-07-05 | Snecma | Dispositif de recuperation d'huile. |
EP2123884B1 (en) * | 2008-05-13 | 2015-03-04 | Rolls-Royce Corporation | Dual clutch arrangement |
US8128021B2 (en) | 2008-06-02 | 2012-03-06 | United Technologies Corporation | Engine mount system for a turbofan gas turbine engine |
US20140174056A1 (en) | 2008-06-02 | 2014-06-26 | United Technologies Corporation | Gas turbine engine with low stage count low pressure turbine |
US20100005810A1 (en) * | 2008-07-11 | 2010-01-14 | Rob Jarrell | Power transmission among shafts in a turbine engine |
US8092093B2 (en) * | 2008-07-31 | 2012-01-10 | General Electric Company | Dynamic impeller oil seal |
US8480527B2 (en) * | 2008-08-27 | 2013-07-09 | Rolls-Royce Corporation | Gearing arrangement |
US8021267B2 (en) * | 2008-12-11 | 2011-09-20 | Rolls-Royce Corporation | Coupling assembly |
US8075438B2 (en) * | 2008-12-11 | 2011-12-13 | Rolls-Royce Corporation | Apparatus and method for transmitting a rotary input into counter-rotating outputs |
US9239012B2 (en) | 2011-06-08 | 2016-01-19 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US9631558B2 (en) | 2012-01-03 | 2017-04-25 | United Technologies Corporation | Geared architecture for high speed and small volume fan drive turbine |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US8572943B1 (en) | 2012-05-31 | 2013-11-05 | United Technologies Corporation | Fundamental gear system architecture |
US20150308351A1 (en) | 2012-05-31 | 2015-10-29 | United Technologies Corporation | Fundamental gear system architecture |
US8756908B2 (en) | 2012-05-31 | 2014-06-24 | United Technologies Corporation | Fundamental gear system architecture |
US9410427B2 (en) * | 2012-06-05 | 2016-08-09 | United Technologies Corporation | Compressor power and torque transmitting hub |
FR2992679A1 (fr) * | 2012-06-28 | 2014-01-03 | Snecma | Tourillon de turbomachine comportant une couronne de recuperation d'un flux d'huile de lubrification avec une pluralite d'orifices d'evacuation d'huile de lubrification |
WO2015094539A1 (en) | 2013-12-16 | 2015-06-25 | United Technologies Corporation | Transfer bearing for geared turbofan |
US9932858B2 (en) | 2015-07-27 | 2018-04-03 | General Electric Company | Gas turbine engine frame assembly |
US10060290B2 (en) | 2015-12-30 | 2018-08-28 | General Electric Company | Method and system for centrifugal pump |
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US11073088B2 (en) | 2019-02-20 | 2021-07-27 | General Electric Company | Gearbox mounting in a turbomachine |
US11753939B2 (en) | 2019-02-20 | 2023-09-12 | General Electric Company | Turbomachine with alternatingly spaced rotor blades |
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US11021970B2 (en) | 2019-02-20 | 2021-06-01 | General Electric Company | Turbomachine with alternatingly spaced rotor blades |
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-
2004
- 2004-10-29 US US10/976,523 patent/US7458202B2/en not_active Expired - Fee Related
-
2005
- 2005-07-25 GB GB0515220A patent/GB2419639B/en not_active Expired - Fee Related
- 2005-07-29 FR FR0508160A patent/FR2877407B1/fr not_active Expired - Fee Related
- 2005-08-18 CA CA2516752A patent/CA2516752C/en not_active Expired - Fee Related
- 2005-08-26 JP JP2005245339A patent/JP4860963B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
GB2419639B (en) | 2009-09-02 |
CA2516752C (en) | 2014-01-07 |
FR2877407B1 (fr) | 2015-10-23 |
CA2516752A1 (en) | 2006-04-29 |
FR2877407A1 (fr) | 2006-05-05 |
US7458202B2 (en) | 2008-12-02 |
US20060090449A1 (en) | 2006-05-04 |
GB2419639A (en) | 2006-05-03 |
JP2006125386A (ja) | 2006-05-18 |
GB0515220D0 (en) | 2005-08-31 |
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