Cryogenic fuel evaporation in compressor of gas turbine
AssigneeMotoren- und Turbinen-Union Munchen GmbH
InventorHermann Hagen
Life of this patent
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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.
Claims5
A gas turbine engine comprising:
- a. a compressor, a combustion engine downstream from the compressor, and a turbine downstream from the combustion chamber,
- b. a supply of liquid hydrogen,
- c. means for injecting hydrogen from the supply into the combustion chamber,
- d. means for injecting the hydrogen in a liquid state into the compressor at a point at least one stage downstream from the compressor intake, said stage being far enough from the compressor outlet so that the hydrogen evaporates before reaching the combustion chamber but the air temperature at said stage being high enough so as to prevent icing of the compressor intake or of the parts of the compressor first stage, and
- e. means for controlling flow of hydrogen to the compressor so that hydrogen is injected into the compressor only when the engine is running above idle speed.
Dependencies are inferred from the claim text.