Cryogenic fuel evaporation in compressor of gas turbine

Details Cryogenic fuel evaporation in compressor of gas turbine Cryogenic fuel evaporation in compressor of gas turbine

1975-03-07

1977-12-13

Freeh, William L.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

60 3946G, 60 3967, 60 3971, F02G 300, F02C 716, F02C 322

Patent

active

040621847

ABSTRACT:
A gas turbine engine having a compressor and a combustion chamber, a supply of liquid hydrogen, and means for injecting the hydrogen in a cryogenic state into the intake of the compressor or into the compressor one or more stages downstream from its intake. Some of the hydrogen may also be injected into the combustion chamber. The hydrogen directed to the combustion chamber may be heated by heat from the engine lubricating oil or hot engine components. Hydrogen may be injected into the compressor only at speeds above idle speed. Hydrogen flow to the compressor may remain substantially constant, but hydrogen flow to the combustion chamber may vary over a wide range.

REFERENCES:
patent: 2602289 (1952-07-01), Anxionnaz et al.
patent: 2630678 (1953-03-01), Pratt
patent: 2689452 (1954-09-01), Jordan
patent: 2718753 (1955-09-01), Bridgeman
patent: 2907527 (1959-10-01), Cummings
patent: 2952974 (1960-09-01), Wright
patent: 2977756 (1961-04-01), Stone
patent: 3263421 (1966-08-01), Londal
patent: 3313103 (1967-04-01), Johnson

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