JP6909242B2 - 受動的凝縮物冷却を有する液体推進剤ロケットエンジン - Google Patents
受動的凝縮物冷却を有する液体推進剤ロケットエンジン Download PDFInfo
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- JP6909242B2 JP6909242B2 JP2018565266A JP2018565266A JP6909242B2 JP 6909242 B2 JP6909242 B2 JP 6909242B2 JP 2018565266 A JP2018565266 A JP 2018565266A JP 2018565266 A JP2018565266 A JP 2018565266A JP 6909242 B2 JP6909242 B2 JP 6909242B2
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- 238000001816 cooling Methods 0.000 title claims description 37
- 239000003380 propellant Substances 0.000 title claims description 31
- 239000007788 liquid Substances 0.000 title claims description 29
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 24
- 239000002184 metal Substances 0.000 claims description 21
- 238000002485 combustion reaction Methods 0.000 claims description 20
- 229910052751 metal Inorganic materials 0.000 claims description 20
- 229910052755 nonmetal Inorganic materials 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 10
- 229920013657 polymer matrix composite Polymers 0.000 claims description 6
- 239000011160 polymer matrix composite Substances 0.000 claims description 4
- 239000004918 carbon fiber reinforced polymer Substances 0.000 claims description 2
- 239000002131 composite material Substances 0.000 claims 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 5
- 229910052799 carbon Inorganic materials 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 239000002826 coolant Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 229910001026 inconel Inorganic materials 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910001092 metal group alloy Inorganic materials 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 229920000642 polymer Polymers 0.000 description 2
- 229910000881 Cu alloy Inorganic materials 0.000 description 1
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000003763 carbonization Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/972—Fluid cooling arrangements for nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/90—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using deflectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
-
- 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
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Nozzles (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
本開示は、2016年6月21日に出願された出願番号第62/352,909号の米国仮特許出願の優先権を主張する。
Claims (16)
- のど部を含む燃焼室と、
のど部の後にあるノズルであって、このノズルは、のど部に隣接した第1ノズル部と、第1ノズル部の後にある第2ノズル部とを含み、第1ノズル部は、能動的冷却要素を含み、第2ノズル部は、能動的冷却要素を含まず、第1ノズル部が、第2ノズル部を受動的に冷却する水凝縮物を形成するように少なくとも能動的冷却要素を介して最適化される、ノズルと、
第1ノズル部の出口端部に設けられ、第1ノズル部で形成された水凝縮物を第2ノズル部へ案内する周方向に離間した流れガイドと、
を備えた液体推進剤ロケットエンジン。 - 能動的冷却要素が、第1ノズル部内の内部通路を含む、請求項1に記載の液体推進剤ロケットエンジン。
- 第1ノズル部が、金属製であり、第2ノズル部が、非金属製である、請求項1に記載の液体推進剤ロケットエンジン。
- 第2ノズル部が、炭素繊維強化ポリマーマトリックス複合材である、請求項3に記載の液体推進剤ロケットエンジン。
- 第1ノズル部が、面積A1を画定する出口を有し、のど部が、面積A2を画定し、比A1/A2が、10以下である、請求項1に記載の液体推進剤ロケットエンジン。
- 第1ノズル部が、面積A1を画定する出口を有し、のど部が、面積A2を画定し、比A1/A2が、8以下である、請求項1に記載の液体推進剤ロケットエンジン。
- 周方向に離間した流れガイドが、ノズルの中心軸線に関して軸方向に細長くなっており、0.2インチ以下の高さを有する、請求項1に記載の液体推進剤ロケットエンジン。
- 周方向に離間した流れガイドが、第1ノズル部から突出したリブである、請求項1に記載の液体推進剤ロケットエンジン。
- 周方向に離間した流れガイドが、直線状である、請求項1に記載の液体推進剤ロケットエンジン。
- 液体推進剤ロケットエンジンであって、
のど部を含む燃焼室と、
のど部の後にあるノズルと、
を備え、燃焼室は、のど部から燃焼生成物を噴出するように作動可能であり、ノズルは、のど部に隣接した金属製ノズル部と、金属製ノズル部の出口にある非金属製ノズル部とを含み、燃焼生成物は、非金属製ノズル部の温度限界を超える、金属製ノズル部の出口における設計温度を有し、金属製ノズル部は、燃焼生成物から水凝縮物を形成するように作動する内部冷却通路を含み、水凝縮物が、非金属製ノズル部を温度限界より下に維持するように非金属製ノズル部と接触し、
金属製ノズル部の出口端部に設けられ、金属製ノズル部で形成された水凝縮物を非金属製ノズル部へ案内する周方向に離間した流れガイドをさらに備えた液体推進剤ロケットエンジン。 - 金属製ノズルの出口が、面積A1を画定し、のど部が、面積A2を画定し、比A1/A2が、10以下である、請求項10に記載の液体推進剤ロケットエンジン。
- 非金属製ノズル部が、ポリマーマトリックス複合材である、請求項11に記載の液体推進剤ロケットエンジン。
- 周方向に離間した流れガイドが、金属製ノズル部から突出したリブである、請求項10に記載の液体推進剤ロケットエンジン。
- 周方向に離間した流れガイドが、ノズルの中心軸線に関して軸方向に細長くなっており、0.2インチ以下の高さを有する、請求項10に記載の液体推進剤ロケットエンジン。
- 周方向に離間した流れガイドが、直線状である、請求項10に記載の液体推進剤ロケットエンジン。
- 金属製ノズル部が、面積A1を画定する出口を有し、のど部が、面積A2を画定し、比A1/A2が、8以下である、請求項11に記載の液体推進剤ロケットエンジン。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201662352909P | 2016-06-21 | 2016-06-21 | |
US62/352,909 | 2016-06-21 | ||
PCT/US2017/037657 WO2017222908A1 (en) | 2016-06-21 | 2017-06-15 | Liquid propellant rocket engine with passive condensate cooling |
Publications (2)
Publication Number | Publication Date |
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JP2019522750A JP2019522750A (ja) | 2019-08-15 |
JP6909242B2 true JP6909242B2 (ja) | 2021-07-28 |
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Application Number | Title | Priority Date | Filing Date |
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JP2018565266A Active JP6909242B2 (ja) | 2016-06-21 | 2017-06-15 | 受動的凝縮物冷却を有する液体推進剤ロケットエンジン |
Country Status (3)
Country | Link |
---|---|
US (1) | US10954892B2 (ja) |
JP (1) | JP6909242B2 (ja) |
WO (1) | WO2017222908A1 (ja) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
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US10876732B2 (en) * | 2016-10-19 | 2020-12-29 | Gloyer-Taylor Laboratories Llc | Scalable acoustically-stable combustion chamber and design methods |
FR3110483B1 (fr) * | 2020-05-20 | 2022-06-03 | Arianegroup Sas | Structure d’assemblage d’une pièce comprenant une première partie métallique et une deuxième partie en matériau composite à matrice organique |
CN111997787A (zh) * | 2020-09-03 | 2020-11-27 | 湖北三江航天江北机械工程有限公司 | 一种自保护特性的导流器 |
CN112539116B (zh) * | 2020-11-12 | 2022-09-13 | 西安长峰机电研究所 | 一种变喉径变扩张比喷管结构 |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4077572A (en) * | 1976-03-25 | 1978-03-07 | Chandler Evans Inc. | Reduced size altitude insensitive thrust vector control nozzle |
US5683033A (en) * | 1989-02-08 | 1997-11-04 | United Technologies Corporation | Rocket nozzle for a rocket engine |
US5582000A (en) * | 1989-02-08 | 1996-12-10 | United Technologies Corporation | Coolable rocket nozzle for a rocket engine |
FR2705738B1 (fr) * | 1993-05-28 | 1995-08-18 | Europ Propulsion | Tuyère de moteur-fusée à diffuseur éjectable. |
US6308514B2 (en) * | 1998-10-28 | 2001-10-30 | Volvo Aero Corporation | Rocket engine nozzle |
DE10157752B4 (de) * | 2001-11-27 | 2006-04-06 | Eads Space Transportation Gmbh | Düsenverlängerung |
US6691948B1 (en) * | 2003-04-10 | 2004-02-17 | The United States Of America As Represented By The Secretary Of The Navy | High torque rocket nozzle |
DE102008061917B4 (de) * | 2008-12-15 | 2010-11-04 | Astrium Gmbh | Heißgaskammer |
FR2947871B1 (fr) | 2009-07-09 | 2011-11-25 | Snecma | Barriere anti-condensation sur circuit regeneratif |
FR2963063B1 (fr) * | 2010-07-26 | 2015-11-27 | Snecma | Chambre de combustion munie d'un element tubulaire |
US8997496B2 (en) * | 2011-06-29 | 2015-04-07 | United Technologies Corporation | Hybrid exhaust component |
FR3011884B1 (fr) | 2013-10-16 | 2018-06-15 | Arianegroup Sas | Chambre de propulsion pour fusee et procede de fabrication d'une telle chambre |
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2017
- 2017-06-15 JP JP2018565266A patent/JP6909242B2/ja active Active
- 2017-06-15 WO PCT/US2017/037657 patent/WO2017222908A1/en active Application Filing
- 2017-06-15 US US16/302,159 patent/US10954892B2/en active Active
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Publication number | Publication date |
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JP2019522750A (ja) | 2019-08-15 |
WO2017222908A1 (en) | 2017-12-28 |
US10954892B2 (en) | 2021-03-23 |
US20190145350A1 (en) | 2019-05-16 |
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