F - Mech Eng,Light,Heat,Weapons – 02 – K
Patent
F - Mech Eng,Light,Heat,Weapons
02
K
60/94, 60/95
F02K 1/12 (2006.01) F02C 7/12 (2006.01) F02K 1/00 (2006.01)
Patent
CA 1065621
COOLING SYSTEM FOR A THRUST VECTORING GAS TURBINE ENGINE EXHAUST NOZZLE Abstract A thrust vectoring gas turbine engine exhaust nozzle is provided with a variable area flow path wherein cooling of the stationary flow path side walls is partially obtained by the film cooling technique. Regulating means, such as a valve, is provided to control the pressure drop of the cooling fluid across the walls as a function of nozzle flow path area, thus optimizing the coolant flow rate as a function of flow path area. Where a rotating bonnet-type deflector is employed to divert the exhaust stream downward to obtain a vertical take-off and landing capability, a system is provided to cool the deflector walls by both the impingement and convection cooling techniques. A favorable pressure gradient for the cooling fluid is obtained by exhausting the cooling fluid to ambient pressure whenever the deflector is deployed. Another valve is provided to regulate the flow of coolant to an expansion flap when the deflector is in its stowed position external to the flow path.
257628
Nash Dudley O.
Wakeman Thomas G.
LandOfFree
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