JP4471644B2 - ガスタービンエンジン推力を発生するための方法及び装置 - Google Patents
ガスタービンエンジン推力を発生するための方法及び装置 Download PDFInfo
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- JP4471644B2 JP4471644B2 JP2003421876A JP2003421876A JP4471644B2 JP 4471644 B2 JP4471644 B2 JP 4471644B2 JP 2003421876 A JP2003421876 A JP 2003421876A JP 2003421876 A JP2003421876 A JP 2003421876A JP 4471644 B2 JP4471644 B2 JP 4471644B2
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- engine
- pulse detonation
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- core engine
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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
- F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
-
- 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
- F02K7/02—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 the jet being intermittent, i.e. pulse-jet
- F02K7/06—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 the jet being intermittent, i.e. pulse-jet with combustion chambers having valves
-
- 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
- F02K7/02—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 the jet being intermittent, i.e. pulse-jet
- F02K7/075—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 the jet being intermittent, i.e. pulse-jet with multiple pulse-jet engines
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Separation By Low-Temperature Treatments (AREA)
- Control Of Turbines (AREA)
Description
Claims (11)
- ガスタービンエンジン(10)用パルスデトネーションシステム(12)であって、
コアエンジン(30)を含み、
前記コアエンジンの下流に位置して前記ガスタービンエンジン内の温度及び圧力を上昇させ且つエンジン推力を発生させるために構成され、
プレデトネータ(48)を有し、多段階で動作するパルスデトネーションオーグメンタ(60)を具備し、
前記プレデトネータ(48)は、第1の動作段階で動作可能であり、前記第1の動作段階では、化学量論比よりも薄い混合気が前記プレデトネータに供給され、該プレデトネータ(48)に燃料が供給されて前記混合気が化学量論比よりも濃くされた後に、該混合気が化学量論比に希釈される、
パルスデトネーションシステム。 - 前記ガスタービンエンジンは、前記コアエンジン(30)の後方向に延出する中心体(50)をさらに有し、
前記プレデトネータ(48)下流には、初期デトネータ(62)が設けられ、
前記パルスデトネーションオーグメンタ(60)は、前記エンジン中心体の周囲に延出する環状チャンバ(64)を更に備え、
前記環状チャンバ(64)は、コアエンジンからのコア空気流と燃料とを混合し、前記コアエンジンの周囲に流れを供給するバイパスダクト(44)からのバイパス空気流と燃料とを混合するミキサ(70)を備え、
第2の動作段階では、前記ミキサの混合気は前記初期デトネータ(62)の下流から放出され、該混合気と前記初期デトネータからの排気ガスとが再点火されることを特徴とする
請求項1記載のパルスデトネーションシステム(12)。 - 前記パルスデトネーションオーグメンタ(60)は、前記ガスタービンエンジン(10)からの調整推力の生成を容易にする請求項1記載のパルスデトネーションシステム(12)。
- 前記ガスタービンエンジン(10)は、前記コアエンジン(30)の後方向に延出する中心体(50)を有し、前記パルスデトネーションオーグメンタ(60)は、前記エンジン中心体の周囲に延出する環状チャンバ(64)を更に備え、
前記環状チャンバ(64)は、コアエンジンからのコア空気流と燃料とを混合し、前記コアエンジンの周囲に流れを供給するバイパスダクト(44)からのバイパス空気流と燃料とを混合するミキサ(70)を備える
請求項1記載のパルスデトネーションシステム(12)。 - 前記環状チャンバ(64)の前記ミキサは、前記エンジン中心体(50)の半径方向外側に位置し、複数の軸方向シュート(74)を備える請求項4記載のパルスデトネーションシステム(12)。
- 前記環状チャンバ(64)の前記ミキサは、前記コアエンジン(30)から流出する流体流れと流通する複数の第1の軸方向シュート(76)と、前記コアエンジンを迂回して流れる流体流れと流通する複数の第2の軸方向シュート(78)とを備える請求項4記載のパルスデトネーションシステム(12)。
- 前記各第1の軸方向シュート(76)は、周囲方向に隣接する一対の前記第2の軸方向シュート(78)の間に位置する請求項6記載のパルスデトネーションシステム(12)。
- 前記パルスデトネーションオーグメンタ(60)は、前記コアエンジン(30)の下流に燃料を供給するための複数の燃料噴霧噴射ノズル(220)を更に備える請求項5記載のパルスデトネーションシステム(12)。
- ガスタービンエンジン(10)であって、
入口部と、
前記入口部と同軸上に位置する排気部と、
前記入口部と前記排気部の間に位置し、前記エンジン内の温度及び圧力を上昇させてエンジン推力を上昇させるために構成され、プレデトネータ(48)を含む多段階で動作するパルスデトネーションオーグメンタ(60)を備えるパルスデトネーションシステム(12)とを具備し、
前記プレデトネータ(48)は、第1の動作段階で動作可能であり、前記第1の動作段階では、化学量論比よりも薄い混合気が前記プレデトネータに供給され、該プレデトネータ(48)に燃料が供給されて前記混合気が化学量論比よりも濃くされた後に、該混合気が化学量論比に希釈されることを特徴とするガスタービンエンジン。 - 前記エンジンに動力を与えるために構成されたコアエンジン(30)と、前記コアエンジンの周囲に流れを供給するバイパスダクト(44)とを更に具備し、前記パルスデトネーションシステム(12)は、前記パルスデトネーションシステムが前記バイパスダクト及び前記コアエンジンと流通するように前記コアエンジンの下流に位置する請求項9記載のガスタービンエンジン(10)。
- 前記コアエンジン(30)の後方向に延出する中心体(50)をさらに有し、
前記プレデトネータ(48)下流には、初期デトネータ(62)が設けられ、
前記パルスデトネーションオーグメンタ(60)は、前記エンジン中心体の周囲に延出する環状チャンバ(64)を更に備え、
前記環状チャンバ(64)は、コアエンジンからのコア空気流と燃料とを混合し、前記コアエンジンの周囲に流れを供給するバイパスダクト(44)からのバイパス空気流と燃料とを混合するミキサ(70)を備え、
第2の動作段階では、前記ミキサの混合気は前記初期デトネータ(62)の下流から放出され、該混合気と前記初期デトネータからの排気ガスとが再点火されることを特徴とする
請求項9に記載のガスタービンエンジン(10)。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/326,343 US6883302B2 (en) | 2002-12-20 | 2002-12-20 | Methods and apparatus for generating gas turbine engine thrust with a pulse detonation thrust augmenter |
Publications (3)
Publication Number | Publication Date |
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JP2004204846A JP2004204846A (ja) | 2004-07-22 |
JP2004204846A5 JP2004204846A5 (ja) | 2007-02-08 |
JP4471644B2 true JP4471644B2 (ja) | 2010-06-02 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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JP2003421876A Expired - Fee Related JP4471644B2 (ja) | 2002-12-20 | 2003-12-19 | ガスタービンエンジン推力を発生するための方法及び装置 |
Country Status (8)
Country | Link |
---|---|
US (1) | US6883302B2 (ja) |
EP (1) | EP1431563B1 (ja) |
JP (1) | JP4471644B2 (ja) |
AT (1) | ATE302901T1 (ja) |
CA (1) | CA2452972C (ja) |
DE (1) | DE60301381T2 (ja) |
ES (1) | ES2247494T3 (ja) |
RU (1) | RU2331784C2 (ja) |
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-
2003
- 2003-12-11 CA CA2452972A patent/CA2452972C/en not_active Expired - Fee Related
- 2003-12-16 ES ES03257930T patent/ES2247494T3/es not_active Expired - Lifetime
- 2003-12-16 EP EP03257930A patent/EP1431563B1/en not_active Expired - Lifetime
- 2003-12-16 AT AT03257930T patent/ATE302901T1/de not_active IP Right Cessation
- 2003-12-16 DE DE60301381T patent/DE60301381T2/de not_active Expired - Lifetime
- 2003-12-19 RU RU2003136814/06A patent/RU2331784C2/ru not_active IP Right Cessation
- 2003-12-19 JP JP2003421876A patent/JP4471644B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
CA2452972C (en) | 2010-01-26 |
ES2247494T3 (es) | 2006-03-01 |
CA2452972A1 (en) | 2004-06-20 |
RU2331784C2 (ru) | 2008-08-20 |
EP1431563A1 (en) | 2004-06-23 |
JP2004204846A (ja) | 2004-07-22 |
EP1431563B1 (en) | 2005-08-24 |
US6883302B2 (en) | 2005-04-26 |
DE60301381D1 (de) | 2005-09-29 |
DE60301381T2 (de) | 2006-06-08 |
US20040118104A1 (en) | 2004-06-24 |
RU2003136814A (ru) | 2005-05-20 |
ATE302901T1 (de) | 2005-09-15 |
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