Detonation cycle gas turbine engine system having intermittent f

Details Detonation cycle gas turbine engine system having intermittent f Detonation cycle gas turbine engine system having intermittent f

1997-12-16

1999-12-14

Kim, Ted

Power plants

Combustion products used as motive fluid

Plural combustion products generators in ring coaxial with...

60 3976, 60 39827, F02C 502

Patent

active

06000214&

ABSTRACT:
A detonation cycle gas turbine engine includes a turbine rotor contained within a housing. Exhaust ports of respective valveless combustion chambers on opposite sides of the rotor direct combustion gases toward the turbine. The chambers are connected by a valveless manifold fed with fuel and oxidizer. When combustible gases are detonated by an igniter in one of the combustion chambers, the back pressure from the detonation shuts off the fuel and oxidizer flow to that chamber and redirects the fuel and oxidizer to the opposite chamber, where detonation occurs, the process repeats cyclically. Power is taken off the rotor shaft mechanically or electrically.

REFERENCES:
patent: 1174439 (1916-03-01), Pelley
patent: 2608058 (1952-08-01), Geeraert
patent: 4254617 (1981-03-01), Papsdorf
patent: 4374288 (1983-02-01), Scragg
patent: 4589398 (1986-05-01), Pate et al.
patent: 4807440 (1989-02-01), Salem
Pratt, G. L., "Experimental Methods", Gas Kinetics, Chapter Two, John Wiley & Sons Ltd., pp. 50-59.

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