Power plants – Reaction motor – Air passage bypasses combustion chamber
Patent
1976-04-29
1977-10-18
Croyle, Carlton R.
Power plants
Reaction motor
Air passage bypasses combustion chamber
60226R, 60224, 60 3933, 415500, 415145, F02K 306, F02K 312
Patent
active
040540308
ABSTRACT:
A variable cycle air breathing gas turbine engine includes a core engine having a combustor, a high pressure turbine stage and a low pressure stage and wherein the high pressure stage drives a compressor for the core engine and the low pressure stage drives a bypass fan for the engine. The low pressure turbine stage includes a row of tip mounted blades located in a first bypass duct and the engine includes auxiliary inlets and crossover valve means for directing air through the first bypass duct during a first mode of engine operation to cause the tip blades on the low pressure turbine stage to operate as an auxiliary bypass fan while the primary fan is driven during the first mode to produce a bypass ratio in a second bypass duct. During a second engine operating mode crossover valve means are conditioned to communicate the first bypass duct with the primary fan and a second combustor element in the first bypass duct is operated to produce flow of motive fluid across the tip blades to drive the blades as a reaction turbine to produce a high temperature turbojet cycle of engine operation.
REFERENCES:
patent: 3002675 (1961-10-01), Howell et al.
patent: 3255585 (1966-06-01), Grieb
patent: 3677012 (1972-07-01), Batscha
patent: 3792584 (1974-02-01), Klees
patent: 3878677 (1975-04-01), Colvin
Croyle Carlton R.
Evans J. C.
Garrett Robert E.
General Motors Corporation
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