发明名称 |
Cooling apparatus for an exhaust nozzle of a gas turbine engine |
摘要 |
A cooling control system for a convergent-divergent gas turbine exhaust nozzle which permits automatic ducting of cooling air during the augmented mode of engine operation. The convergent flaps of the nozzle have longitudinal ducts embedded therein with a pair of openings near the aft extreme of each of the convergent flaps and openings located in the forward half of the convergent flaps. The convergent seals overlap the convergent flaps and are slideably mounted for positioning over the aft openings on the flaps. A positive pressure is generated under the convergent flap liner and seal liner when the convergent seal is opened to allow cooling air to be ducted through the flap. The positive pressure forces the convergent flap and seal liners up toward the center line of the nozzle.
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申请公布号 |
US4203286(A) |
申请公布日期 |
1980.05.20 |
申请号 |
US19780956305 |
申请日期 |
1978.10.30 |
申请人 |
U S OF AMERICA AIR FORCE SECRETARY |
发明人 |
WARBURTON, ROBERT E |
分类号 |
F02K1/12;F02K1/80;F02K1/82;(IPC1-7):F02K1/12 |
主分类号 |
F02K1/12 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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