JP4920228B2 - ガスタービンエンジンを組み立てるための方法及び装置 - Google Patents
ガスタービンエンジンを組み立てるための方法及び装置 Download PDFInfo
- Publication number
- JP4920228B2 JP4920228B2 JP2005283188A JP2005283188A JP4920228B2 JP 4920228 B2 JP4920228 B2 JP 4920228B2 JP 2005283188 A JP2005283188 A JP 2005283188A JP 2005283188 A JP2005283188 A JP 2005283188A JP 4920228 B2 JP4920228 B2 JP 4920228B2
- Authority
- JP
- Japan
- Prior art keywords
- flade
- duct
- stream
- engine
- inner fan
- 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
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Classifications
-
- 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
- F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- 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
- F02K3/075—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 controlling flow ratio between flows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
20 フレード入口
22 ファン入口
26 フレードダクト
28 ファンダクト
30 ファンケーシング
32 フレードケーシング
34 ファン組立体
40 ファンブレード
60 シュラウド
74 フレードストリーム
86 ファンダクトの下流端部
88 フレード式ファン組立体
90 フレード式ロータブレード
110 フレードストリーム・オーグメンタ
112 ノズル組立体
130 フレードダクト・スクロール
140 燃料噴霧バー
142 バーナ
144 バーナ空洞
Claims (8)
- その一部分を通して空気流を流すための内側ファンダクト(28)と、前記内側ファンダクト内に配置された少なくとも1つの列の内側ファンブレード(40)を有する少なくとも1つの内側ファンセクション(34)とを備えたコアエンジンを含むガスタービンエンジン(12)用のフレードシステムであって、
前記内側ファンダクトを囲みかつフレードストリーム(26)を形成するフレードダクト(26)と、
前記内側ファンセクションの半径方向外側に位置しかつ前記内側ファンセクションによって駆動されるように該内側ファンセクションに結合された少なくとも1つの列のフレード式ファンブレード(90)を含む、前記フレードダクト内に配置されかつフレードストリーム空気流(74)を生成する少なくとも1つのフレード式ファン(88)と、
前記フレードダクト内に配置されたフレードストリーム・オーグメンタ(110)と、
前記フレードストリーム空気流(74)の一部分を前記フレードストリーム・オーグメンタ(110)の上流に流すためのフレードダクト・スクロール(130)と
を含み、
前記フレードストリーム・オーグメンタ(110)が、燃料噴霧バー(140)、バーナ(142)及び前記バーナの下流に位置するバーナ空洞(144)を含み、
前記エンジン(12)が、前記バーナ空洞の面積の拡大及び縮小を行うことが可能なストラット(166)を含む
ことを特徴とする、フレードシステム。 - 前記フレードダクト(26)が、前記内側ファンダクト(28)の周りに流れた空気流流出の少なくとも一部分を捕捉するように構成されている、請求項1記載のフレードシステム。
- 前記フレードストリーム・オーグメンタ(110)が、前記フレードストリーム空気流(74)の一部分を燃焼させることによって前記エンジン(12)のスラストを増大させるのを可能にする、請求項1記載のフレードシステム。
- 前記エンジン(12)が、前記コアエンジンの下流に配置された排気ノズル組立体(112)を含み、該フレードシステムが、前記フレードストリーム(74)の一部分が前記排気ノズルを通って排出されるように該排気ノズルと流れ連通状態になっている、請求項1記載のフレードシステム。
- 前記フレードストリーム・オーグメンタ(110)が、前記フレードストリーム(74)内部の温度上昇を引き起こして前記エンジン(12)のノズルベースドラグを低減するのを可能にするように構成されている、請求項1記載のフレードシステム。
- 前記フレードダクト(26)は、上部セクション(134)及び下部セクション(132)を含み、前記フレードダクト・スクロール(130)が、前記上部及び下部セクションの一方から他方に向けて前記フレードストリーム空気流(74)の20〜30%を流すことを特徴とする、請求項1乃至5のいずれか1項に記載のフレードシステム。
- その一部分を通して空気流を流すための内側ファンダクト(28)と、前記内側ファンダクト内に配置された少なくとも1つの列の内側ファンブレード(40)を有する少なくとも1つの内側ファンセクション(34)とを備えたコアエンジンと、
フレードシステムと
を含むガスタービンエンジン(12)であって、
前記フレードシステムは、
前記コアエンジンを囲みかつフレードストリーム(74)を形成するフレードダクト(26)と、
前記内側ファンセクションの半径方向外側に位置しかつ前記内側ファンセクションによって駆動されるように該内側ファンセクションに結合された少なくとも1つの列のフレード式ファンブレード(90)を含む、前記フレードダクト内に配置されかつフレードストリーム空気流を生成する少なくとも1つのフレード式ファン(88)と、
前記フレードダクト内に配置されたフレードストリーム・オーグメンタ(110)と、
前記フレードストリーム空気流(74)の一部分を前記フレードストリーム・オーグメンタ(110)の上流に流すためのフレードダクト・スクロール(130)と
を含み、
前記フレードストリーム・オーグメンタ(110)が、燃料噴霧バー(140)、バーナ(142)及び前記バーナの下流に位置するバーナ空洞(144)を含み、
前記エンジン(12)が、前記バーナ空洞の面積の拡大及び縮小を行うことが可能なストラット(166)を含む
ことを特徴とする、ガスタービンエンジン(12)。 - 前記フレードダクト(26)は、上部セクション(134)及び下部セクション(132)を含み、前記フレードダクト・スクロール(130)が、前記上部及び下部セクションの一方から他方に向けて前記フレードストリーム空気流(74)の20〜30%を流すことを特徴とする、請求項7記載のガスタービンエンジン(12)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/955,614 US7188467B2 (en) | 2004-09-30 | 2004-09-30 | Methods and apparatus for assembling a gas turbine engine |
US10/955,614 | 2004-09-30 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2006105138A JP2006105138A (ja) | 2006-04-20 |
JP4920228B2 true JP4920228B2 (ja) | 2012-04-18 |
Family
ID=35311518
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005283188A Expired - Fee Related JP4920228B2 (ja) | 2004-09-30 | 2005-09-29 | ガスタービンエンジンを組み立てるための方法及び装置 |
Country Status (4)
Country | Link |
---|---|
US (1) | US7188467B2 (ja) |
EP (1) | EP1643114A2 (ja) |
JP (1) | JP4920228B2 (ja) |
CA (1) | CA2520471C (ja) |
Families Citing this family (20)
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FR2866070B1 (fr) * | 2004-02-05 | 2008-12-05 | Snecma Moteurs | Turboreacteur a fort taux de dilution |
WO2007037725A1 (en) * | 2005-09-27 | 2007-04-05 | Volvo Aero Corporation | An arrangement for propelling an aircraft, aircraft and outlet nozzle for a jet engine |
US20070134087A1 (en) * | 2005-12-08 | 2007-06-14 | General Electric Company | Methods and apparatus for assembling turbine engines |
US7926290B2 (en) * | 2006-12-18 | 2011-04-19 | General Electric Company | Turbine engine with modulated flow fan and method of operation |
US7770381B2 (en) * | 2006-12-18 | 2010-08-10 | General Electric Company | Duct burning mixed flow turbofan and method of operation |
RU2343301C2 (ru) * | 2007-01-12 | 2009-01-10 | Геннадий Степанович Николаев | Газожидкостный реактивный двигатель |
DE102008017143A1 (de) | 2007-04-16 | 2008-10-23 | Luk Lamellen Und Kupplungsbau Beteiligungs Kg | Mitnehmereinheit für eine Kupplungsanordnung, insbesondere eine nasslaufende Doppelkupplungsanordnung |
US8739548B2 (en) * | 2007-12-20 | 2014-06-03 | United Technologies Corporation | Sliding ramp nozzle system for a gas turbine engine |
US20110171007A1 (en) * | 2009-09-25 | 2011-07-14 | James Edward Johnson | Convertible fan system |
US20110167792A1 (en) * | 2009-09-25 | 2011-07-14 | James Edward Johnson | Adaptive engine |
US9353684B2 (en) * | 2009-12-11 | 2016-05-31 | Northrop Grumman Systems Corporation | Aircraft engine airflow modulation apparatus and method for engine bay cooling and cycle flow matching |
US8777554B2 (en) * | 2009-12-21 | 2014-07-15 | General Electric Company | Intermediate fan stage |
US8844262B2 (en) * | 2009-12-29 | 2014-09-30 | Rolls-Royce North American Technologies, Inc. | Exhaust for a gas turbine engine |
US9016041B2 (en) * | 2010-11-30 | 2015-04-28 | General Electric Company | Variable-cycle gas turbine engine with front and aft FLADE stages |
US8984891B2 (en) | 2010-12-30 | 2015-03-24 | General Electric Company | Flade discharge in 2-D exhaust nozzle |
US9863366B2 (en) * | 2013-03-13 | 2018-01-09 | Rolls-Royce North American Technologies Inc. | Exhaust nozzle apparatus and method for multi stream aircraft engine |
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US10371090B2 (en) | 2014-01-13 | 2019-08-06 | United Technologies Corporation | Variable area exhaust mixer for a gas turbine engine |
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-
2004
- 2004-09-30 US US10/955,614 patent/US7188467B2/en active Active
-
2005
- 2005-09-22 CA CA2520471A patent/CA2520471C/en not_active Expired - Fee Related
- 2005-09-26 EP EP05255971A patent/EP1643114A2/en not_active Withdrawn
- 2005-09-29 JP JP2005283188A patent/JP4920228B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
EP1643114A2 (en) | 2006-04-05 |
US20060064961A1 (en) | 2006-03-30 |
JP2006105138A (ja) | 2006-04-20 |
US7188467B2 (en) | 2007-03-13 |
CA2520471C (en) | 2013-08-13 |
CA2520471A1 (en) | 2006-03-30 |
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