JP2004204846A - 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
- Publication number
- JP2004204846A JP2004204846A JP2003421876A JP2003421876A JP2004204846A JP 2004204846 A JP2004204846 A JP 2004204846A JP 2003421876 A JP2003421876 A JP 2003421876A JP 2003421876 A JP2003421876 A JP 2003421876A JP 2004204846 A JP2004204846 A JP 2004204846A
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- Japan
- Prior art keywords
- engine
- pulse detonation
- detonation system
- gas turbine
- augmentor
- 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.)
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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
Landscapes
- 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)
Abstract
【解決手段】 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)はコアエンジン(30)を含む。パルスデトネーションシステムはコアエンジンの下流に位置し、ガスタービン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増加させるために構成される。パルスデトネーションシステムは、化学量論的混合気がプレデトネータに提供される少なくとも第1の動作段階で動作可能なプレデトネータ(48)を備える多段パルスデトネーションオーグメンタ(60)を有する。
【選択図】図1
Description
Claims (10)
- 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、化学量論比よりも少ない混合気がプレデトネータに供給される少なくとも第1の動作段階で動作可能なプレデトネータ(48)を有する多段パルスデトネーションオーグメンタ(60)を具備するパルスデトネーションシステム。
- 前記オーグメンタ(60)は、化学量論的混合気が前記オーグメンタに供給される少なくとも第2の動作段階で更に動作可能である請求項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燃焼チャンバ(64)を更に備える請求項1記載のパルスデトネーションシステム(12)。
- 前記環状燃焼チャンバ(64)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)。
- 前記環状燃焼チャンバ(64)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、化学量論比よりも少ない混合気がオーグメンタに供給される少なくとも第1の動作段階で動作可能なプレデトネータ(48)を含む多段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)。
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 |
---|---|
JP2004204846A true JP2004204846A (ja) | 2004-07-22 |
JP2004204846A5 JP2004204846A5 (ja) | 2007-02-08 |
JP4471644B2 JP4471644B2 (ja) | 2010-06-02 |
Family
ID=32393120
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
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) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
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JP2011080448A (ja) * | 2009-10-09 | 2011-04-21 | General Electric Co <Ge> | 液体燃料式パルスデトネーションエンジンの低温始動のためのプレナム空気予熱 |
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US7140174B2 (en) * | 2004-09-30 | 2006-11-28 | General Electric Company | Methods and apparatus for assembling a gas turbine engine |
US7818956B2 (en) * | 2005-05-13 | 2010-10-26 | General Electric Company | Pulse detonation assembly and hybrid engine |
US7591129B2 (en) * | 2005-12-29 | 2009-09-22 | Kenneth Erwin Worrell | Rotary piston engine |
US7634904B2 (en) * | 2006-01-09 | 2009-12-22 | General Electric Company | Methods and apparatus to facilitate generating power from a turbine engine |
WO2007099046A1 (de) * | 2006-02-28 | 2007-09-07 | Siemens Aktiengesellschaft | Gasturbinenbrenner und verfahren zum betreiben eines gasturbinenbrenners |
US7552796B2 (en) * | 2006-04-27 | 2009-06-30 | United Technologies Corporation | Turbine engine tailcone resonator |
FR2905975B1 (fr) * | 2006-09-20 | 2008-12-05 | Snecma Sa | Conduite de soufflante pour une turbomachine. |
US7950219B2 (en) * | 2006-10-31 | 2011-05-31 | General Electric Company | Dual mode combustion operation of a pulse detonation combustor in a hybrid engine |
US7748211B2 (en) * | 2006-12-19 | 2010-07-06 | United Technologies Corporation | Vapor cooling of detonation engines |
US8266889B2 (en) * | 2008-08-25 | 2012-09-18 | General Electric Company | Gas turbine engine fan bleed heat exchanger system |
US20100077726A1 (en) * | 2008-09-30 | 2010-04-01 | General Electric Company | Plenum air preheat for cold startup of liquid-fueled pulse detonation engines |
US8377232B2 (en) * | 2009-05-04 | 2013-02-19 | General Electric Company | On-line cleaning of turbine hot gas path deposits via pressure pulsations |
US8429893B2 (en) | 2009-08-11 | 2013-04-30 | Northrop Grumman Corporation | Airflow modulation for dual mode combined cycle propulsion systems |
US8973365B2 (en) * | 2010-10-29 | 2015-03-10 | Solar Turbines Incorporated | Gas turbine combustor with mounting for Helmholtz resonators |
RU2489595C1 (ru) * | 2011-11-24 | 2013-08-10 | Александр Юрьевич Соколов | Тяговый модуль постоянного детонационного горения паровоздушной топливной смеси |
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RU2573438C1 (ru) * | 2014-08-07 | 2016-01-20 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Способ форсирования авиационных двигателей |
WO2016157224A1 (en) * | 2015-04-03 | 2016-10-06 | MAUTONE BARROS, Jose Eduardo | Engine for hypersonic aircrafts with supersonic combustor |
RU2613755C1 (ru) * | 2015-09-23 | 2017-03-21 | Федеральное Государственное Унитарное Предприятие Тушинское Машиностроительное Конструкторское Бюро "Союз" | Турбопрямоточный воздушно-реактивный двигатель |
US10221763B2 (en) | 2016-12-23 | 2019-03-05 | General Electric Company | Combustor for rotating detonation engine and method of operating same |
RU2674172C1 (ru) * | 2017-07-11 | 2018-12-05 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Турбореактивный двигатель и способ его работы |
US10823126B2 (en) | 2018-08-31 | 2020-11-03 | General Electric Company | Combustion-powered flow control actuator with external fuel injector |
US11236908B2 (en) | 2018-10-24 | 2022-02-01 | General Electric Company | Fuel staging for rotating detonation combustor |
US11371711B2 (en) | 2018-11-28 | 2022-06-28 | General Electric Company | Rotating detonation combustor with offset inlet |
US11105511B2 (en) | 2018-12-14 | 2021-08-31 | General Electric Company | Rotating detonation propulsion system |
RU2724559C1 (ru) * | 2019-09-19 | 2020-06-23 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение ("ПАО "ОДК-УМПО") | Турбореактивный авиационный двигатель |
US11572840B2 (en) | 2019-12-03 | 2023-02-07 | General Electric Company | Multi-mode combustion control for a rotating detonation combustion system |
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- 2002-12-20 US US10/326,343 patent/US6883302B2/en not_active Expired - Lifetime
-
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 JP JP2003421876A patent/JP4471644B2/ja not_active Expired - Fee Related
- 2003-12-19 RU RU2003136814/06A patent/RU2331784C2/ru not_active IP Right Cessation
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2011080448A (ja) * | 2009-10-09 | 2011-04-21 | General Electric Co <Ge> | 液体燃料式パルスデトネーションエンジンの低温始動のためのプレナム空気予熱 |
Also Published As
Publication number | Publication date |
---|---|
CA2452972A1 (en) | 2004-06-20 |
ES2247494T3 (es) | 2006-03-01 |
RU2331784C2 (ru) | 2008-08-20 |
EP1431563B1 (en) | 2005-08-24 |
JP4471644B2 (ja) | 2010-06-02 |
ATE302901T1 (de) | 2005-09-15 |
EP1431563A1 (en) | 2004-06-23 |
DE60301381D1 (de) | 2005-09-29 |
CA2452972C (en) | 2010-01-26 |
DE60301381T2 (de) | 2006-06-08 |
US20040118104A1 (en) | 2004-06-24 |
RU2003136814A (ru) | 2005-05-20 |
US6883302B2 (en) | 2005-04-26 |
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