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An exhaust nozzle assembly provides fluidic thrust vectoring of the primary stream to enhance aircraft maneuverability. The exhaust nozzle assembly includes a cooling air passage that supplies cooling air to a plurality of cooling holes that generate an insulating layer of air. A vector slot injects cooling airflow into the exhaust passage normal to the primary stream. A cover plate partially blocks the vector slot to direct cooling airflow into the exhaust passage that in turn directs portions of the primary stream.

InventoresJack T. Blozy, Charles M. Willard, Nathan L. Messersmith, Miquel A. Velazquez
Cesionario originalUnited Technologies Corporation
Examinador principal: William H Rodriguez
Abogado: Carlson, Gaskey & Olds
Clasificación actual de EE.UU.60/228; 239/265.19

Ver patente en USPTO
Buscar en base de datos de cesión de patentes de USPTO

Citas

Patente citada Fecha de presentación Fecha de emisión Cesionario original Título
US32943232 Jul 196427 Dic 1966JET DEFLECTOR DEVICE OPERATING BY LIQUID INJECTION
US329679927 Ago 19651967THRUST VECTOR CONTROL SYSTEM
US33546453 Ene 196628 Nov 1967METHOD AND APPARATUS FOR PRODUCING A NON-AXIAL THRUST VECTOR
US33707948 Nov 196527 Feb 1968ANNULAR PLENUM NOZZLE FOR CONTROLLING TRAJECTORY OF ROCKETS
US340922810 Feb 19665 Nov 1968EJECTOR NOZZLE
US35634677 Sep 19661 Feb 1971ROCKET MOTOR THRUST NOZZLES
US368739911 May 197029 Ago 1972VARIABLE AREA EXHAUST NOZZLE
US37493171 Mar 19713 Jul 1973THRUST VECTOR CONTROL SYSTEM
US381911725 May 19701974THRUST VECTOR X J JET INTERACTION
US470645312 Nov 198617 Nov 1987General Motors CorporationSupport and seal assembly
US471887022 Nov 198512 Ene 1988Techmet CorporationMarine propulsion system
US483645110 Sep 19876 Jun 1989United Technologies CorporationYaw and pitch convergent-divergent thrust vectoring nozzle
US497807111 Abr 198918 Dic 1990General Electric CompanyNozzle with thrust vectoring in the yaw direction
US526160411 May 199216 Nov 1993General Electric CompanyYaw vectoring blade
US535188814 May 19934 Oct 1994General Electric CompanyMulti-axis vectorable exhaust nozzle
US55773816 Dic 199426 Nov 1996United Technologies CorporationExhaust nozzle cooling scheme for gas turbine engine
US56879073 Jul 198918 Nov 1997United Technologies CorporationYaw and pitch thrust vectoring nozzle
US57066509 Ago 199513 Ene 1998United Technologies CorporationVectoring nozzle using injected high pressure air
US582679428 Feb 199727 Oct 1998The Boeing CompanyAircraft scoop ejector nozzle
US586322911 Jun 199626 Ene 1999Bombardier, Inc.Variable venturi
US58848434 Nov 199623 Mar 1999The Boeing CompanyEngine noise suppression ejector nozzle
US590815924 Feb 19971 Jun 1999The Boeing CompanyAircraft chute ejector nozzle
US599693629 Sep 19977 Dic 1999General Electric CompanyFluidic throat exhaust nozzle
US602163729 Sep 19978 Feb 2000General Electric CompanyIntegrated fluidic CD nozzle for gas turbine engine
US633631926 May 20008 Ene 2002General Electric CompanyFluidic nozzle control system
US636052831 Oct 199726 Mar 2002General Electric CompanyChevron exhaust nozzle for a gas turbine engine
US64706693 Ene 200229 Oct 2002Lockheed Martin CorporationHybrid injection thrust vector control
US667904818 Dic 200220 Ene 2004Lockheed Martin CorporationApparatus and method for controlling primary fluid flow using secondary fluid flow injection
US2006028318826 Jun 2006Suppression of part of the noise from a gas turbine engine

Citada por

Patente citante Fecha de presentación Fecha de emisión Cesionario original Título
US756579725 Feb 200528 Jul 2009GHKN Engineering LLCSystems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles
US784969517 Sep 200114 Dic 2010Alliant Techsystems Inc.Rocket thruster comprising load-balanced pintle valve
US821509713 Dic 201010 Jul 2012Alliant Techsystems Inc.Rocket thruster assembly comprising load-balanced pintle valve

Reclamaciones

1. An exhaust nozzle assembly for fluidic vectoring of a primary stream comprising:

an exhaust passage for directing a primary stream;

a duct wall defining an airflow passage for cooling air;

a vector slot within said duct wall open to said exhaust passage providing a flow of cooling air from said airflow passage into said exhaust passage; wherein said vector slot is arc shaped having an apex and distal ends, said apex disposed downstream of said distal ends; and

a cover movable for blocking a portion of said flow of cooling air from said airflow passage into said exhaust passage for selectively directing said primary stream.

2. The assembly as recited in claim 1, wherein said exhaust passage comprises a trailing edge and said apex is disposed closer to said trailing edge than said distal ends.

3. The assembly as recited in claim 1, wherein said slot is of a constant width.

4. The assembly as recited in claim 1, including an actuator arm attached to said cover for selectively positioning said cover over a portion of said vector slot.

5. The assembly as recited in claim 4, wherein said cover selectively directs said flow of cooling air into said exhaust passage to provide yaw vectoring.

6. The assembly as recited in claim 1, wherein the flow of cooling air through said vector slot is normal to a primary jet stream through said exhaust passage.

7. An exhaust nozzle assembly for fluidic vectoring of a primary stream comprising:

an exhaust passage for directing a primary stream, wherein said exhaust passage is rectangular;

a duct wall defining an airflow passage for cooling air;

a vector opening within said duct wall open to said exhaust passage providing a flow of cooling air from said airflow passage into said exhaust passage; and

a cover smaller than said vector opening such that some portion of the vector opening is always open for providing a flow of cooling air into exhaust passage regardless of a position of said cover, said cover movable for blocking a portion of said flow of cooling air from said airflow passage into said exhaust passage for selectively directing said primary stream.

8. An exhaust nozzle assembly for fluidic vectoring of a primary stream comprising:

an exhaust passage for directing a primary stream;

a duct wall defining an airflow passage for cooling air;

a vector opening within said duct wall open to said exhaust passage providing a flow of cooling air from said airflow passage into said exhaust passage, wherein said vector opening comprises a plurality of vector holes disposed within an arc having an apex and distal ends; and

a cover movable for blocking a portion of said flow of cooling air from said airflow passage into said exhaust passage for selectively directing said primary stream.

9. The assembly as recited in claim 8, wherein said apex is disposed downstream of said distal ends.

10. The assembly as recited in claim 8, wherein said duct wall includes a plurality of cooling holes for said cooling air, wherein said plurality of vector holes are larger than said plurality of cooling holes.

11. The assembly as recited in claim 7, wherein a width of said exhaust passage is approximately nine times a height of said exhaust passage.

12. The assembly as recited in claim 1, wherein said exhaust passage includes a top side, a bottom side and first and second sides between said top side and bottom side, wherein said vector slot is disposed within one of said top side and bottom side.

13. A fluidic vectoring assembly for an exhaust nozzle comprising:

a cover plate movable within a cooling air passage for selectively blocking a portion of a vector opening, wherein the vector opening is arc shaped for communicating an arc shaped flow of cooling air to an exhaust passage, and said cover plate blocks a portion of cooling air flow into the exhaust passage to modify a direction of flow of a primary stream.

14. The assembly as recited in claim 13, including an actuator arm attached to said cover plate for moving said cover plate to different portions of said vector opening.

15. The assembly as recited in claim 13, wherein said cover plate blocks an equal area of the vector opening for all positions of the cover plate.

16. The assembly as recited in claim 13, wherein said cover selectively directs the flow of cooling air into the exhaust passage to provide fluidic vectoring of the primary stream.