US20060225426A1 - Turobjet axisymmetric nozzle controlled hot flap shutter - Google Patents
Turobjet axisymmetric nozzle controlled hot flap shutter Download PDFInfo
- Publication number
- US20060225426A1 US20060225426A1 US10/941,806 US94180604A US2006225426A1 US 20060225426 A1 US20060225426 A1 US 20060225426A1 US 94180604 A US94180604 A US 94180604A US 2006225426 A1 US2006225426 A1 US 2006225426A1
- Authority
- US
- United States
- Prior art keywords
- flap shutter
- controlled hot
- friction surface
- flap
- hot flap
- 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.)
- Granted
Links
Images
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
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
-
- 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
- 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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
-
- 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
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
- F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
-
- 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
-
- 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
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Baking, Grill, Roasting (AREA)
- Gasket Seals (AREA)
- Laminated Bodies (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Lift Valve (AREA)
Abstract
Description
- The invention relates to a variable ejection cross-section ejection nozzle, mounted on the downstream end of a fixed circular cross-section structure of a turbojet hot gas ejection channel, particularly for military aircraft.
- Some military aircraft equipped with turbojets must be able to carry out missions under subsonic or supersonic flight conditions. Therefore, these turbojets are equipped with a heating system and an axisymmetric or other type nozzle, two-dimensional, for example. For turbo-engines equipped with heating systems, the nozzle must have a variable cross-section. As a result, the flap shutters of the inner ejection channel, referred to as “hot flap shutters”, are therefore each mounted pivoting around an axis perpendicular to the turbojet axis, tangent to a diameter which is close to the ejection diameter.
- Each of said flap shutters is controlled for pivoting by a common synchronized tilting device. Between each controlled hot flap shutter, there is a tracking flap shutter which is not controlled and wherein the orientation is carried out by the two controlled hot flap shutters adjacent thereto. Therefore, each tracking flap shutter has lateral parts subject to friction with a controlled hot flap shutter.
- In addition, at this level of the hot gas ejection channel, there is a nozzle seal which is in contact with each of the tracking flap shutters and the controlled hot flap shutters.
- However, the various pivoting movements of the flap shutters induce wear due to friction, particularly at the upstream contact zone between each flap shutter and the nozzle gasket(s). In fact, it is important to note that these flap shutters are made of a ceramic matrix composite material. However, the nozzle seals are made of metal.
- In other words, rapid and mutual wear problems relating to the nozzle seal and the flap shutter friction surface, due to relative friction, occur at the trailing edge of the nozzle and the flap shutter hinge pin, thus affecting the service life of the nozzle components.
- In addition, the use of ceramic matrix composite materials requires these flap shutters to only have very low radii of curvature, i.e. angular shapes. This is a drawback for the tightness between each tracking flap shutter and said two adjacent controlled hot flap shutters. In effect, with reference to
FIG. 1 , while thetracking flap shutter 1 may have a compact shape, this is not the case for the controlledhot flap shutter 2 which takes on a deformed sheet shape. This results in a relativelylarge gap 4 being created between the lateral edge of thetracking flap shutter 1 and the surface of the controlledhot flap shutter 2 and the external surface of thenozzle seal 3. - The invention aims to remedy these drawbacks.
- To this end, the main subject of the invention is a turbojet axisymmetric nozzle controlled hot flap shutter, pivoting around an axis perpendicular to the turbojet axis, comprising:
- a ceramic composite material flap shutter plate; and
- a friction surface placed widthways under the flap shutter plate and intended to remain in contact with a nozzle seal, said seal being made of metal.
- According to the invention, the friction surface is made of metal.
- In this way, the metal/metal contact of said surface with respect to the nozzle seal generates much less wear at this point.
- In order to improve the tightness between a tracking flap shutter, the adjacent control hot flap shutter and the nozzle seal, the friction surface is limited laterally by two lateral flanks roughly perpendicular to the friction surface and intended to be positioned opposite and close to the lateral flanks of the adjacent tracking flap shutters.
- In a first preferential embodiment of the invention, the friction surface is integrated in the controlled hot flap shutter.
- Preferentially, this integration of the friction surface in the controlled hot flap shutter is carried out during the casting of the controlled hot flap shutter.
- In a second embodiment, the friction surface is an added part attached to the controlled hot flap shutter.
- In this case, the attachment may be made using assembly screws holding a friction surface support part between the flap shutter plate and a flap shutter frame.
- The invention and its different technical characteristics will be understood more clearly on reading the following detailed description of two embodiments of the invention.
- They are accompanied by several figures representing respectively:
-
FIG. 1 , a sectional view, already described, of the junction between a tracking flap shutter and a controlled hot flap shutter according to the prior art; -
FIG. 2 , a cavalier view of a controlled hot flap shutter according to a first embodiment of the invention; -
FIG. 3 , two controlled hot flap shutters surrounding a tracking flap shutter according to the first embodiment of the invention; -
FIG. 4 , an exploded view of a controlled hot flap shutter according to a second embodiment of the invention; and -
FIG. 5 , the junction between a tracking flap shutter and a controlled hot flap shutter according to the invention. - With reference to
FIG. 2 , a first embodiment of the controlled hot flap shutter is as follows. Amain body 29 opposite two parallel reinforcements supports on each side abush 21 intended to receive the flap shutter control lever. The lower part of thebody 29 comprises apivoting hole 26 around the axis from which the flap shutter pivots. The lower part also comprises abearing plate 27 intended to receive the additional shape of aflap shutter plate 22 consisting of a heat-resistant material such as a ceramic matrix composite. The rear lower part, just below one end of theflap shutter plate 22, comprises atapered friction surface 24, with a slightly convex cross-section. In addition, length ways, it is slightly dished so as to show a slightly concave shape widthways on the flap shutter. It is limited laterally by twolateral flanks 25 which are perpendicular to the tapered shape shown by saidfriction surface 24. - In this embodiment, the
flap shutter plate 22 is an integral part of the flap shutter. In effect, it is inserted into agroove 28 above thefriction surface 24 and is attached during the manufacture of thebearing plate 27 of the flap shutter, particularly during the casting. A large proportion of the controlled hot flap shutter is made of metal, while theflap shutter plate 22 is made of ceramic matrix composite material. -
FIG. 3 contains two controlledhot flap shutters 20 surrounding atracking flap shutter 10. Eachflap shutter plate 22 of the controlledhot flap shutters 20 laterally overlaps the correspondingflap shutter plate 12 of thetracking flap shutter 10. In order to improve the tightness of all the flap shutter bases, at theirfriction surface 24 for the controlledhot flap shutters tracking flap shutters 10, the edges orlateral flanks 25 of eachfriction surface 24 of the controlledhot flap shutters 20 must be located as close as possible to the corresponding adjacentlateral flanks 15 of the adjacenttracking flap shutters 10. However, given that thelateral flanks 25 of thefriction surfaces 24 are perpendicular to said surfaces, as a result, at eachflap shutter plate 22, thelateral flanks 25 of the controlledhot flap shutters 20 and thelateral flanks 15 of thetracking flap shutters 10 can be positioned opposite each other while being practically parallel and therefore very close.FIG. 4 allows a clearer understanding, compared toFIG. 1 , of the improvement of the tightness at this point. In effect, thelateral flanks 15 of thetracking flap shutters hot flap shutters 20 are very close to each other and thegap 4 inFIG. 1 is considerably reduced, which improves the tightness of the assembly at this point. - The embodiment represented in
FIG. 5 shows aflap shutter plate 32 which is intended to be attached to its controlledhot flap shutter 40 by means ofseveral assembly screws 41 andnuts 42. In this case, thecontact surface 44 is supported by asupport part 47 which is not attached to theframe 49 of the controlledhot flap shutter 40 during the manufacture thereof. On the contrary, it represents a separate part and is machined to form an added metal part. It is easy to envisage that, with attachment means, such asassembly screws 41,corresponding nuts 42 andpassage holes 43 in thesupport part flap shutter frame flap shutter plate 32, the assembly can be attached and disassembled independently from the manufacture of the assembly. - Naturally, the geometry of the
support part 47 and of thefriction surface 44 and the lateral flanks in particular must correspond to those described above in the first embodiment. In this second embodiment, the same advantages related to wear on thefriction surfaces 44, with respect to the nozzle seal and gasket at the same point, are obtained.
Claims (6)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0350577 | 2003-09-19 | ||
FR0350577A FR2860046B1 (en) | 2003-09-19 | 2003-09-19 | HOT PIPE CONTROL OF AXISYMETRIC TUYERE TURBOJET ENGINE |
Publications (2)
Publication Number | Publication Date |
---|---|
US7117682B1 US7117682B1 (en) | 2006-10-10 |
US20060225426A1 true US20060225426A1 (en) | 2006-10-12 |
Family
ID=34179005
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/941,806 Active 2024-11-27 US7117682B1 (en) | 2003-09-19 | 2004-09-16 | Turbojet axisymmetric nozzle controlled hot flap shutter |
Country Status (10)
Country | Link |
---|---|
US (1) | US7117682B1 (en) |
EP (1) | EP1517032B1 (en) |
JP (1) | JP2005121009A (en) |
KR (1) | KR20050028789A (en) |
CN (1) | CN1607323A (en) |
CA (1) | CA2480538A1 (en) |
DE (1) | DE602004004025T2 (en) |
ES (1) | ES2278280T3 (en) |
FR (1) | FR2860046B1 (en) |
RU (1) | RU2344307C2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080117922A1 (en) * | 2006-11-16 | 2008-05-22 | Sbc Knowledge Ventures, Lp | Home automation system and method including remote media access |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7458221B1 (en) * | 2003-10-23 | 2008-12-02 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Variable area nozzle including a plurality of convexly vanes with a crowned contour, in a vane to vane sealing arrangement and with nonuniform lengths |
FR2873757B1 (en) * | 2004-07-28 | 2006-09-29 | Snecma Moteurs Sa | CONVERGENT TUYERE OF TURBOREACTOR |
FR2891272B1 (en) * | 2005-09-28 | 2009-07-10 | Snecma Sa | METHOD OF PROTECTING THE WEAR OF A THERMOSTRUCTURAL PIECE OF COMPOSITE MATERIAL WITH CERAMIC MATRIX, COATING AND PIECE OBTAINED BY THIS METHOD. |
US7555904B1 (en) * | 2006-09-29 | 2009-07-07 | United Technologies Corporation | Thermally compliant rivet connection for connecting turbine engine liner to convergent flap and seal for turbine nozzle |
US8122722B2 (en) * | 2008-02-29 | 2012-02-28 | General Electric Company | Exhaust nozzle seal with segmented basesheet disposed between side rails |
IL190022A (en) * | 2008-03-09 | 2014-01-30 | Israel Aerospace Ind Ltd | Apparatus and method for controlling a vehicle and vehicle controlled thereby |
FR2929998B1 (en) * | 2008-04-14 | 2011-08-12 | Aircelle Sa | DOUBLE FLOW TURBOREACTOR NACELLE |
US8607577B2 (en) * | 2009-11-24 | 2013-12-17 | United Technologies Corporation | Attaching ceramic matrix composite to high temperature gas turbine structure |
US10012104B2 (en) | 2014-10-14 | 2018-07-03 | United Technologies Corporation | Gas turbine engine convergent/divergent nozzle with unitary synchronization ring for roller track nozzle |
CN111520253B (en) * | 2020-04-30 | 2021-07-27 | 玉环天润航空机械制造有限公司 | Jet engine structure for airplane based on wind power change |
Citations (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4128208A (en) * | 1977-07-11 | 1978-12-05 | General Electric Company | Exhaust nozzle flap seal arrangement |
US4637550A (en) * | 1985-10-01 | 1987-01-20 | The United States Of America As Represented By The Secretary Of The Air Force | Dual material exhaust nozzle flap |
US4641783A (en) * | 1983-12-21 | 1987-02-10 | Societe Nationale D'etude Et De Construction De Meteur D'aviation (Snecma) | Exhaust nozzle assembly for a turbojet engine |
US4878618A (en) * | 1988-12-08 | 1989-11-07 | United Technologies Corporation | Wear resistant, self-damping clamp assembly |
US5110050A (en) * | 1974-09-07 | 1992-05-05 | Rolls-Royce (1971) Limited | Gas turbine engine nozzle |
US5215257A (en) * | 1992-07-16 | 1993-06-01 | United Technologies Corporation | Divergent seal arrangement for a convergent/divergent nozzle |
US5232158A (en) * | 1992-08-11 | 1993-08-03 | United Technologies Corporation | Convergent/divergent nozzle with seal centering |
US5261605A (en) * | 1990-08-23 | 1993-11-16 | United Technologies Corporation | Axisymmetric nozzle with gimbled unison ring |
US5269467A (en) * | 1992-08-03 | 1993-12-14 | General Electric Company | Vectoring exhaust nozzle seal and flap retaining apparatus |
US5285637A (en) * | 1992-11-02 | 1994-02-15 | United Technologies Corporation | Seal centering and restraining device for an axisymmetric convergent/divergent nozzle |
US5437411A (en) * | 1992-12-14 | 1995-08-01 | General Electric Company | Vectoring exhaust nozzle flap and seal positioning apparatus |
US5484105A (en) * | 1994-07-13 | 1996-01-16 | General Electric Company | Cooling system for a divergent section of a nozzle |
US5485959A (en) * | 1991-05-16 | 1996-01-23 | General Electric Company | Axisymmetric vectoring exhaust nozzle thermal shield |
US5676312A (en) * | 1994-08-18 | 1997-10-14 | Societe National D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) | Seal for a variable geometry nozzle |
US5683034A (en) * | 1995-05-22 | 1997-11-04 | United Technologies Corporation | Engine exhaust nozzle seal |
US5779152A (en) * | 1997-01-16 | 1998-07-14 | General Electric Company | Coordinated vectoring exhaust nozzle with scissors linkage |
US5794850A (en) * | 1996-09-27 | 1998-08-18 | United Technologies Corporation | Enclosed pressure balanced sync ring nozzle |
US5839663A (en) * | 1996-07-23 | 1998-11-24 | United Technologies Corporation | Gas turbine exhaust nozzle flap and flap seal apparatus |
US20020079404A1 (en) * | 2000-12-22 | 2002-06-27 | Schroeder Wayne K. | Method and apparatus for planar actuation of a flared surface to control a vehicle |
US6745570B2 (en) * | 2002-02-01 | 2004-06-08 | General Electric Co. | Methods and apparatus for sealing gas turbine engine nozzles using a flap system |
US20050132709A1 (en) * | 2003-12-19 | 2005-06-23 | Gould Kenneth A. | Exhaust nozzle segmented basesheet and production method thereof |
US20050210861A1 (en) * | 2004-03-26 | 2005-09-29 | Bush Robert H | Axial divergent section slot nozzle |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2704599B1 (en) * | 1993-04-29 | 1995-06-09 | Snecma | VARIABLE GEOMETRY EJECTION NOZZLE FOR TURBOMACHINE. |
-
2003
- 2003-09-19 FR FR0350577A patent/FR2860046B1/en not_active Expired - Fee Related
-
2004
- 2004-09-14 CA CA002480538A patent/CA2480538A1/en not_active Abandoned
- 2004-09-14 KR KR1020040073328A patent/KR20050028789A/en not_active Application Discontinuation
- 2004-09-15 JP JP2004268178A patent/JP2005121009A/en not_active Withdrawn
- 2004-09-16 ES ES04104481T patent/ES2278280T3/en active Active
- 2004-09-16 EP EP04104481A patent/EP1517032B1/en active Active
- 2004-09-16 DE DE602004004025T patent/DE602004004025T2/en active Active
- 2004-09-16 US US10/941,806 patent/US7117682B1/en active Active
- 2004-09-17 RU RU2004127904/06A patent/RU2344307C2/en active
- 2004-09-20 CN CNA2004100780438A patent/CN1607323A/en active Pending
Patent Citations (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5110050A (en) * | 1974-09-07 | 1992-05-05 | Rolls-Royce (1971) Limited | Gas turbine engine nozzle |
US4128208A (en) * | 1977-07-11 | 1978-12-05 | General Electric Company | Exhaust nozzle flap seal arrangement |
US4641783A (en) * | 1983-12-21 | 1987-02-10 | Societe Nationale D'etude Et De Construction De Meteur D'aviation (Snecma) | Exhaust nozzle assembly for a turbojet engine |
US4637550A (en) * | 1985-10-01 | 1987-01-20 | The United States Of America As Represented By The Secretary Of The Air Force | Dual material exhaust nozzle flap |
US4878618A (en) * | 1988-12-08 | 1989-11-07 | United Technologies Corporation | Wear resistant, self-damping clamp assembly |
US5261605A (en) * | 1990-08-23 | 1993-11-16 | United Technologies Corporation | Axisymmetric nozzle with gimbled unison ring |
US5485959A (en) * | 1991-05-16 | 1996-01-23 | General Electric Company | Axisymmetric vectoring exhaust nozzle thermal shield |
US5215257A (en) * | 1992-07-16 | 1993-06-01 | United Technologies Corporation | Divergent seal arrangement for a convergent/divergent nozzle |
US5269467A (en) * | 1992-08-03 | 1993-12-14 | General Electric Company | Vectoring exhaust nozzle seal and flap retaining apparatus |
US5232158A (en) * | 1992-08-11 | 1993-08-03 | United Technologies Corporation | Convergent/divergent nozzle with seal centering |
US5285637A (en) * | 1992-11-02 | 1994-02-15 | United Technologies Corporation | Seal centering and restraining device for an axisymmetric convergent/divergent nozzle |
US5437411A (en) * | 1992-12-14 | 1995-08-01 | General Electric Company | Vectoring exhaust nozzle flap and seal positioning apparatus |
US5484105A (en) * | 1994-07-13 | 1996-01-16 | General Electric Company | Cooling system for a divergent section of a nozzle |
US5676312A (en) * | 1994-08-18 | 1997-10-14 | Societe National D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) | Seal for a variable geometry nozzle |
US5683034A (en) * | 1995-05-22 | 1997-11-04 | United Technologies Corporation | Engine exhaust nozzle seal |
US5839663A (en) * | 1996-07-23 | 1998-11-24 | United Technologies Corporation | Gas turbine exhaust nozzle flap and flap seal apparatus |
US5794850A (en) * | 1996-09-27 | 1998-08-18 | United Technologies Corporation | Enclosed pressure balanced sync ring nozzle |
US5779152A (en) * | 1997-01-16 | 1998-07-14 | General Electric Company | Coordinated vectoring exhaust nozzle with scissors linkage |
US20020079404A1 (en) * | 2000-12-22 | 2002-06-27 | Schroeder Wayne K. | Method and apparatus for planar actuation of a flared surface to control a vehicle |
US6745570B2 (en) * | 2002-02-01 | 2004-06-08 | General Electric Co. | Methods and apparatus for sealing gas turbine engine nozzles using a flap system |
US20050132709A1 (en) * | 2003-12-19 | 2005-06-23 | Gould Kenneth A. | Exhaust nozzle segmented basesheet and production method thereof |
US6935118B2 (en) * | 2003-12-19 | 2005-08-30 | General Electric Company | Exhaust nozzle segmented basesheet and production method thereof |
US20050210861A1 (en) * | 2004-03-26 | 2005-09-29 | Bush Robert H | Axial divergent section slot nozzle |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080117922A1 (en) * | 2006-11-16 | 2008-05-22 | Sbc Knowledge Ventures, Lp | Home automation system and method including remote media access |
Also Published As
Publication number | Publication date |
---|---|
ES2278280T3 (en) | 2007-08-01 |
CA2480538A1 (en) | 2005-03-19 |
US7117682B1 (en) | 2006-10-10 |
RU2344307C2 (en) | 2009-01-20 |
EP1517032B1 (en) | 2007-01-03 |
EP1517032A1 (en) | 2005-03-23 |
DE602004004025T2 (en) | 2007-07-12 |
FR2860046A1 (en) | 2005-03-25 |
CN1607323A (en) | 2005-04-20 |
JP2005121009A (en) | 2005-05-12 |
FR2860046B1 (en) | 2005-12-02 |
DE602004004025D1 (en) | 2007-02-15 |
KR20050028789A (en) | 2005-03-23 |
RU2004127904A (en) | 2006-02-27 |
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AS | Assignment |
Owner name: SNECMA MOTEURS, FRANCE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SEVI, GUILLAUME;BLANCHARD, STEPHANE;PANCOU, THIERRY;REEL/FRAME:016165/0778 Effective date: 20040903 |
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Owner name: SNECMA MOTEURS, FRANCE Free format text: CORRECTED COVER SHEET TO CORRECT ASSIGNEE'S ADDRESS, PREVIOUSLY RECORDED AT REEL/FRAME 016165/0778 (ASSIGNMENT OF ASSIGNOR'S INTEREST);ASSIGNORS:SEVI, GUILLAUME;BLANCHARD, STEPHANE;PANCOU, THIERRY;REEL/FRAME:016805/0802 Effective date: 20040903 |
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STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
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