Gas turbine engine turbine system

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

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416 96R, F01D 518

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active

059416874

ABSTRACT:
When cooling air from a gas turbine engine compressor is supplied in greater quantities than is needed, the flow thereof is reduced firstly and mainly by ensuring that the air leaves a blade stage cooling thereby at a radius less than that of its entry. A pressure head results which slows the cooling air flow rate prior to its entering a plenum chamber defined by the disc of the stage and fixed structure. There is a reduced tendency of the air to enter the gas stream.

REFERENCES:
patent: 2920865 (1960-01-01), Lombard
patent: 3712756 (1973-01-01), Kalikow et al.
patent: 4447190 (1984-05-01), Campbell
patent: 4818178 (1989-04-01), Sibbertsen

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