WO2008075671A1 - ジェット噴流排気ノズル及びジェットエンジン - Google Patents
ジェット噴流排気ノズル及びジェットエンジン Download PDFInfo
- Publication number
- WO2008075671A1 WO2008075671A1 PCT/JP2007/074295 JP2007074295W WO2008075671A1 WO 2008075671 A1 WO2008075671 A1 WO 2008075671A1 JP 2007074295 W JP2007074295 W JP 2007074295W WO 2008075671 A1 WO2008075671 A1 WO 2008075671A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- jet
- partition wall
- cylindrical partition
- facing
- exhaust nozzle
- Prior art date
Links
- 238000005192 partition Methods 0.000 claims abstract description 58
- 238000011144 upstream manufacturing Methods 0.000 claims description 16
- 230000002093 peripheral effect Effects 0.000 claims description 14
- 239000000567 combustion gas Substances 0.000 claims description 8
- 239000000446 fuel Substances 0.000 claims description 7
- 230000001154 acute effect Effects 0.000 claims description 5
- 239000012530 fluid Substances 0.000 description 7
- 230000000052 comparative effect Effects 0.000 description 5
- 238000013459 approach Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000007599 discharging Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
- F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
- B64D33/06—Silencing exhaust or propulsion jets
Definitions
- the present invention relates to a jet jet exhaust nozzle and a jet engine.
- An aircraft jet engine includes a fan that takes in air, a compressor that takes in a portion of the air taken in by the fan and compresses it, and a combustor that mixes and burns the air and fuel compressed by the compressor.
- the fan and the turbine that drives the compressor are sequentially arranged by the combustion gas of the combustor.
- the compressor, the combustor, and the turbine are disposed in the cylindrical partition wall, and the fan is disposed on the upstream side of the cylindrical partition wall. Most of the air taken in by the fan passes through a bypass channel provided between the casing and the casing covering the outer periphery of the cylindrical partition wall. The air (bypass flow) that has passed through this bypass flow path is discharged so as to surround the outer periphery of the turbine exhaust (core flow), and merges with the core flow.
- Patent Documents 1 to 3 disclose mixers that reduce jet noise by efficiently mixing the core flow and the bypass flow.
- the mixer described in Patent Document 1 has a plurality of triangular pyramids arranged at the downstream end of the cylindrical partition wall. This triangular pyramid is alternately attached to the outer peripheral surface and the inner peripheral surface with one side of the bottom surface aligned with the downstream end of the cylindrical partition wall.
- the two side surfaces forming the ridge line directed to the upstream side of the triangular pyramid can exchange a part of the high-speed internal flow (ie, the core flow) and the low-speed external flow (ie, the bypass flow) with each other. Since it is guided in the direction of! /, The fluid flowing inside and outside the cylindrical partition is efficiently mixed, reducing jet noise.
- Patent Document 1 Japanese Patent Laid-Open No. 2003-172205
- Patent Document 2 Japanese Patent Laid-Open No. 2000-80958
- Patent Document 3 U.S. Pat.No. 6,826,901
- the noise factor generated by the jet engine is due to the influence of a bi-facing (also referred to as a pylon) for mounting the jet engine on the fuselage.
- a bi-facing also referred to as a pylon
- the noise caused by this bifacing will be described with reference to Fig. 8.
- Z is a core flow
- Y is a bypass flow
- X is air flowing outside the bypass flow Y (external airflow).
- the flow velocity is the slowest in the external airflow X, where the core flow z is the fastest, followed by the bypass flow Y.
- the present invention has been made in view of the above-described circumstances, and an object of the present invention is to reduce noise by preventing the presence of bi-facing from affecting the intensification of noise.
- a cylindrical partition As a first means, a cylindrical partition, a cylindrical casing covering the outer periphery of the cylindrical partition, and the axial direction of the cylindrical partition and the casing are provided. And a bifurcation that supports the cylindrical partition wall and each downstream end of the casing from the outside.
- the cylindrical partition wall is a flow path through which a high-speed core flow flows.
- a jet-jet exhaust nozzle in which a low-speed bypass flow flows between a single singe and is located in the vicinity of the bifurcation at the downstream edge of the cylindrical partition wall and in a symmetrical position across the bifacial.
- 1st projection force A structure is used that is arranged inside the secondary vortex generation area on both sides of the bifacing.
- the jet jet exhaust nozzle according to the first or second means adopts a structure in which the first protrusion protrudes toward the inner peripheral side of the cylindrical partition wall.
- the jet jet exhaust nozzle is provided with an interval in the circumferential direction of the downstream edge of the cylindrical partition wall, and the upstream side
- the structure further includes a plurality of second protrusions that are inclined so as to form an acute angle with the axial direction toward the downstream side and project toward the inner peripheral side and / or the outer peripheral side of the cylindrical partition wall.
- the first protrusion and the second protrusion which are provided on the bi-facility side, Adopted a structure in which a larger number than the one provided on the anti-bifurcation side is provided
- the first protrusion is a triangular pyramid with one of the ridges facing upstream. Adopted.
- the second protrusion has a structure in which one of the ridge lines is a triangular pyramid facing upstream. Adopted.
- a fan that takes in air
- a compressor that compresses air taken in by the fan
- a combustor that mixes and burns fuel into the air compressed by the compressor.
- a jet engine having a jet jet exhaust nozzle according to any one of the first to eighth aspects, and a bifa A jet engine that is disposed so as to protrude downward with respect to the wing and attached to the wing so that the suspension is supported by the bi-facing was adopted.
- a fan that takes in air
- a compressor that compresses the air taken in by the fan
- a fuel mixed with the air compressed by the compressor is burned.
- a turbine that drives a fan and a compressor with combustion gas of the combustor, and includes a jet jet exhaust nozzle according to any one of the first to eighth aspects.
- the jet engine is installed so that the bi-facing protrudes to the side of the aircraft and can be supported by the bi-facing cantilever.
- the pair of first protrusions are provided in the vicinity of the bi-facing and symmetrically across the bi-facing, so that the core flow is guided in the vicinity of the bi-facing by these first protrusions. And can be mixed efficiently with the bypass flow. Therefore, it is possible to reduce the noise by preventing the presence of bi-facing from affecting the intensification of noise.
- the secondary vortices are likely to generate noise due to these first protrusions.
- the core flow can be guided inside the generation area. Therefore, noise can be reduced by preventing the presence of bi-facing from affecting the intensification of noise.
- the first protrusions are protruded toward the inner peripheral side of the cylindrical partition wall, so that these first protrusions cause an inward force as the core flow proceeds downstream. Therefore, the core flow becomes closer to the external airflow. Therefore, noise can be reduced by preventing the presence of bi-facing from affecting the intensification of noise.
- FIG. 1 is a schematic cross-sectional view showing a schematic configuration of a jet engine according to a first embodiment of the present invention.
- FIG. 2 is a cross-sectional view of the jet engine according to the first embodiment of the present invention, taken along line aa in FIG. 1, as viewed from the downstream side.
- FIG. 3 is a perspective view showing an appearance of a notch (first protrusion) in the first embodiment of the present invention.
- FIG. 4 is a graph showing the relationship between speed and noise in the first embodiment of the present invention.
- FIG. 5 is a cross-sectional view of a jet engine, which is a comparative example of the first embodiment of the present invention, viewed from the downstream side.
- FIG. 6 is a perspective view showing an appearance of a notch (second protrusion) in a modification of the first embodiment of the present invention.
- FIG. 7 is a cross-sectional view of a jet engine according to a second embodiment of the present invention, viewed from the downstream side, corresponding to FIG. 2 in the first embodiment.
- FIG. 8 is a schematic diagram showing the core flow, bypass flow, and external air flow exhausted by conventional jet engine power.
- FIG. 1 is a schematic cross-sectional view showing a schematic configuration of a jet engine 100 in the present embodiment.
- the jet engine 100 includes a nozzle 1 (jet jet exhaust nozzle), a fan 2, a compressor 3, a combustor 4, and a turbine 5.
- the nozzle 1 includes a casing 11, a cylindrical partition wall 12, and a bifurcation 13.
- the casing 11 and the cylindrical partition wall 12 are cylindrical members.
- the casing 11 forms the outer shape of the jet engine 100 and covers the outer periphery of the cylindrical partition wall 12.
- the cylindrical partition wall 12 is disposed slightly downstream in the axial direction with respect to the casing 11, and partitions the flow path through which the core flow Z flows and the flow path through which the bypass flow Y flows.
- the core flow Z is a high-speed fluid that flows in the cylindrical partition wall 12
- the bypass flow Y is a low-speed fluid that flows between the cylindrical partition wall 12 and the casing 11.
- the bifurcation 13 is a member extending along the axial direction of the casing 11 and the cylindrical partition wall 12, and supports the downstream ends of the casing 11 and the cylindrical partition wall 12 from the outside.
- the bi-facing 13 is disposed so as to protrude downward with respect to the wing of the aircraft.
- the jet engine 100 is attached to the wing so as to be supported by being suspended by the bi-facing unit 13.
- the fan 2, the compressor 3, the combustor 4, and the turbine 5 are sequentially arranged from the upstream side to the downstream side in the nozzle 1.
- the fan 2 is disposed in the vicinity of the upstream end in the casing 11 and upstream of the cylindrical partition wall 12 and takes in air A from the outside.
- the compressor 3 is disposed near the upstream end in the cylindrical partition wall 12 and takes in a part of the air A taken in by the fan 2 and compresses it.
- the combustor 4 is disposed on the downstream side of the compressor 3 in the cylindrical partition wall 12.
- the combustor 4 mixes and burns fuel with the air A compressed by the compressor 3, and discharges the combustion gas.
- the turbine 5 is disposed on the downstream side of the combustor 4 in the cylindrical partition wall 12, and drives the fan 2 and the compressor 3 by the combustion gas discharged from the combustor 4.
- An opening on the upstream side of the casing 11 is an air intake port 14 for taking in air A.
- An opening on the downstream side of the casing 11 is a bypass flow discharge port 15 for discharging the bypass flow Y.
- the bypass flow Y is the air A that has not been taken into the compressor 3 out of the air A taken from the air intake 14.
- the opening on the downstream side of the cylindrical partition wall 12 is a core flow outlet 16 for discharging the core flow Z.
- the core flow Z is the exhaust from the turbine 5, that is, the combustion gas.
- the symbol X indicates the external airflow.
- the external air flow X is air that flows outside the bypass flow Y through the outside of the casing 11.
- FIG. 2 is a cross-sectional view as seen from the downstream side of the jet engine 100, and is a cross-sectional view taken along the line aa in FIG.
- Secondary vortices are generated on both sides of bifaction 13.
- Range of secondary vortex generation (secondary vortex generation area) SI and S2 are bifaque when the width of the bi-facing 13 is about 300 mm, for example, and the radius of the core flow outlet 16 is about 300 mm, for example. -The range from the center line C of 13 to about 36 ° in the circumferential direction of the bypass flow outlet 15.
- notches 21 and 22 are provided on the downstream edge 12a of the cylindrical partition wall 12a.
- the notches 21 and 22 are symmetrical positions with the bi-facing 13 in between, and are provided inside the secondary vortex generation region.
- each ridge line is bypassed from the center line C of the bi-facing 13 It is provided so as to be located at a position shifted by approximately 31 ° in the circumferential direction of the flow outlet 15.
- notches 31, 32, 33 are provided on the downstream edge 12 a of the cylindrical partition wall 12.
- the notches 31 and 32 are provided so that each ridge line is located at a position shifted from the center line C of the bi-facility 13 by approximately 81 ° in the circumferential direction of the bypass flow outlet 15. That is, the downstream edge 12a of the cylindrical partition 12 is connected to the bi-facility side B and the anti-bi-facility by a virtual line segment L orthogonal to the center line C of the bi-facing 13 and passing through the center of the cylindrical partition 12. When notched into side b, notches 31 and 32 are located on the noise side B.
- the notch 33 is provided such that the ridge line is located at a position shifted from the center line C of the bi-facility 13 by approximately 180 ° in the circumferential direction of the bypass flow outlet 15. In other words, the notch 33 is located on the anti-bifacing side b.
- the positions of the notches 31, 32, 33 are distributed so that many are provided on the bi-facility side B.
- the notch 21 (same as the notches 22, 31, 32, 33) is formed by folding and projecting the downstream edge 12a of the cylindrical partition wall 12 to the inner peripheral side.
- fluid guide surfaces 21b and 21c such as two side surfaces of a triangular pyramid with the ridge line 21a facing upstream are formed.
- the jet engine 100 having such a configuration performs a known operation. That is, fan 2 takes in air A from air intake 14, and compressor 3 compresses a part of air A taken in by fan 2. Then, the combustor 4 mixes fuel with the air A compressed by the compressor 3 and burns it, and the turbine 5 drives the fan 2 and the compressor 3 with the combustion gas discharged from the combustor 4.
- the core flow Z flows into the cylindrical partition wall 12 and the bypass flow Y flows between the cylindrical partition wall 12 and the casing 11.
- the core flow Z and the bypass flow Y are mixed by the notches 21, 22, 31, 32, 33.
- Notch 21 (same for notch 22) is guided by fluid guide surfaces 21b and 21c so that the core flow Z discharged from the core flow discharge port 16 moves away from the secondary vortex generation areas SI and S2 as it goes downstream. To do. As a result, the core flow Z becomes closer to the external air flow X, so that the noise is reduced.
- FIG. 4 shows the relationship between speed and noise, as well as the noise (1) of the conventional jet engine, the noise (2) of the jet engine 100 of the present embodiment, and the jet of the comparative example shown in FIG. engine
- the comparative example of (3) is a notch 41 having the same shape as the notch 21 and others of this embodiment.
- the noise (2) in this embodiment is 2d at maximum.
- the comparative example (3) is not only less effective in reducing noise than the conventional (1).
- the notch 21 is considered in consideration of the influence of the noise 13.
- the notch 21 (22, 31, 32, 33) is protruded by folding the downstream edge 12a of the cylindrical partition wall 12 to the inner peripheral side.
- the notches 31 (21, 22, 32, 33) may be formed so as to protrude to the outer peripheral side.
- five notches 21, 22, 31, 31, 32, 33 are provided. More notches may be formed. In this case, for example, if the notches provided on the anti-bifurcation side are formed so as to protrude alternately on the inner peripheral side and the outer peripheral side, the core flow Z and the bypass flow Y can be effectively mixed.
- FIG. 7 is a cross-sectional view of the jet engine 300 according to the present embodiment as viewed from the downstream side, and corresponds to FIG. 2 in the first embodiment.
- the same members as those in the first embodiment are denoted by the same reference numerals.
- the bi-facing 13 of the jet engine 300 is arranged so that the center line C is substantially horizontal and protrudes laterally with respect to the aircraft body. Accordingly, the jet engine 300 is attached to the airframe so as to be cantilevered by the bi-facing unit 13.
- the notches 21 and 22 are located at positions where the ridge lines are shifted from the center line C of the bifac- sion 13 by approximately 31 ° in the circumferential direction of the bypass flow outlet 15 as in the first embodiment. It is provided.
- the notch 31 is provided so that the ridge line is located at a position shifted from the center line C of the bi-facility 13 by approximately 90 ° in the circumferential direction of the bypass flow outlet 15.
- the notch 32 is provided such that the ridge line is located at a position shifted by approximately 225 ° in the circumferential direction of the bypass flow outlet 15 from the center line C of the bifurcation 13.
- the notch 33 is provided so as to be positioned approximately between the notch 32 and the notch 22! /.
- the notches 21, 22, 31, 32, 33 are arranged as described above, so that many notches are arranged on the ground side when the jet engine 300 is divided into two horizontally.
- the first protrusion and the second protrusion are the first protrusion and the second protrusion when the force is described as the notches 2 1, 22, 31, 32, 33 that are triangular pyramids.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP07850783.7A EP2123894B1 (en) | 2006-12-18 | 2007-12-18 | Jet flow discharge nozzle and corresponding jet engine |
US12/519,558 US8418437B2 (en) | 2006-12-18 | 2007-12-18 | Jet flow discharge nozzle and jet engine |
CA2673001A CA2673001C (en) | 2006-12-18 | 2007-12-18 | Jet flow discharge nozzle and jet engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2006-340066 | 2006-12-18 | ||
JP2006340066A JP4830836B2 (ja) | 2006-12-18 | 2006-12-18 | ジェット噴流排気ノズル及びジェットエンジン |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2008075671A1 true WO2008075671A1 (ja) | 2008-06-26 |
Family
ID=39536301
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2007/074295 WO2008075671A1 (ja) | 2006-12-18 | 2007-12-18 | ジェット噴流排気ノズル及びジェットエンジン |
Country Status (5)
Country | Link |
---|---|
US (1) | US8418437B2 (ja) |
EP (1) | EP2123894B1 (ja) |
JP (1) | JP4830836B2 (ja) |
CA (1) | CA2673001C (ja) |
WO (1) | WO2008075671A1 (ja) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011125248A1 (ja) * | 2010-04-09 | 2011-10-13 | 株式会社Ihi | ジェット噴流ノズル及びジェットエンジン |
CN102438752A (zh) * | 2009-03-31 | 2012-05-02 | 吉坤日矿日石能源株式会社 | 一氧化碳选择性氧化反应用催化剂的制造方法 |
JP2012233429A (ja) * | 2011-04-28 | 2012-11-29 | Ihi Corp | ジェットエンジン |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8087250B2 (en) * | 2008-06-26 | 2012-01-03 | General Electric Company | Duplex tab exhaust nozzle |
JP5446749B2 (ja) * | 2009-11-09 | 2014-03-19 | 株式会社Ihi | エンジン排気ノズル及び航空機エンジン |
JP5446783B2 (ja) * | 2009-11-27 | 2014-03-19 | 株式会社Ihi | エンジン排気ノズル及び航空機エンジン |
JP5572060B2 (ja) * | 2010-10-22 | 2014-08-13 | 株式会社やまびこ | 送風作業機 |
US9783315B2 (en) * | 2012-02-24 | 2017-10-10 | Rohr, Inc. | Nacelle with longitudinal translating cowling and rotatable sleeves |
FR2993921B1 (fr) * | 2012-07-26 | 2014-07-18 | Snecma | Procede pour ameliorer les performances du systeme d'ejection d'un turbomoteur d'aeronef a double flux separes, systeme d'ejection et turbomoteur correspondants. |
JP6035946B2 (ja) | 2012-07-26 | 2016-11-30 | 株式会社Ihi | エンジンダクト及び航空機エンジン |
DE102012219541A1 (de) * | 2012-10-25 | 2014-04-30 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Düse, Strukturelement und Verfahren zur Herstellung einer Düse |
JP6102648B2 (ja) * | 2013-09-13 | 2017-03-29 | ソニー株式会社 | 情報処理装置及び情報処理方法 |
JP6437745B2 (ja) * | 2014-06-20 | 2018-12-12 | 株式会社マキタ | ノズル |
US10094332B2 (en) * | 2014-09-03 | 2018-10-09 | The Boeing Company | Core cowl for a turbofan engine |
WO2020097608A1 (en) * | 2018-11-09 | 2020-05-14 | Jetoptera, Inc. | Adaptive vertical take-off and landing propulsion system |
WO2022140040A2 (en) * | 2020-12-03 | 2022-06-30 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Methods and apparatuses for reducing engine noise |
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JP4325397B2 (ja) | 2003-12-25 | 2009-09-02 | 株式会社豊田自動織機 | 傾斜スイッチ取付構造 |
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US8157207B2 (en) * | 2006-08-09 | 2012-04-17 | The Boeing Company | Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods |
US7520124B2 (en) * | 2006-09-12 | 2009-04-21 | United Technologies Corporation | Asymmetric serrated nozzle for exhaust noise reduction |
US7963099B2 (en) * | 2007-05-21 | 2011-06-21 | General Electric Company | Fluted chevron exhaust nozzle |
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- 2007-12-18 WO PCT/JP2007/074295 patent/WO2008075671A1/ja active Application Filing
- 2007-12-18 CA CA2673001A patent/CA2673001C/en active Active
- 2007-12-18 US US12/519,558 patent/US8418437B2/en active Active
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JPH04325397A (ja) * | 1991-04-25 | 1992-11-13 | Mitsubishi Heavy Ind Ltd | 多発航空機 |
US6532729B2 (en) * | 2001-05-31 | 2003-03-18 | General Electric Company | Shelf truncated chevron exhaust nozzle for reduction of exhaust noise and infrared (IR) signature |
JP2003172205A (ja) * | 2001-12-07 | 2003-06-20 | Ishikawajima Harima Heavy Ind Co Ltd | ジェット噴流用ミキサ |
JP2005030404A (ja) * | 2003-07-09 | 2005-02-03 | Snecma Moteurs | タービンエンジンの噴射ノイズの軽減装置 |
JP2006029328A (ja) * | 2004-07-13 | 2006-02-02 | Snecma Moteurs | ジェットノイズを低減するためのターボ機械ノズルカバー |
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Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102438752A (zh) * | 2009-03-31 | 2012-05-02 | 吉坤日矿日石能源株式会社 | 一氧化碳选择性氧化反应用催化剂的制造方法 |
WO2011125248A1 (ja) * | 2010-04-09 | 2011-10-13 | 株式会社Ihi | ジェット噴流ノズル及びジェットエンジン |
JPWO2011125248A1 (ja) * | 2010-04-09 | 2013-07-08 | 株式会社Ihi | ジェット噴流ノズル及びジェットエンジン |
US9140210B2 (en) | 2010-04-09 | 2015-09-22 | Ihi Corporation | Jet flow nozzle and jet engine |
JP2012233429A (ja) * | 2011-04-28 | 2012-11-29 | Ihi Corp | ジェットエンジン |
Also Published As
Publication number | Publication date |
---|---|
JP4830836B2 (ja) | 2011-12-07 |
CA2673001C (en) | 2012-04-24 |
EP2123894A1 (en) | 2009-11-25 |
US20100031628A1 (en) | 2010-02-11 |
EP2123894A4 (en) | 2011-03-16 |
CA2673001A1 (en) | 2008-06-26 |
US8418437B2 (en) | 2013-04-16 |
JP2008151033A (ja) | 2008-07-03 |
EP2123894B1 (en) | 2016-08-03 |
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