Aerodynamic loading in gas turbine engines

Details Aerodynamic loading in gas turbine engines Aerodynamic loading in gas turbine engines

1989-06-07

1991-01-15

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

60722, F02C 720

Patent

active

049844237

ABSTRACT:
This invention provides a means for reacting the axial loads F.sub.A experienced by for example, the combustion chamber inner and outer casings 24, 30 and the inlet guide vanes of 26 of the turbine of a gas turbine engine, through the outlet guide vanes 22 of the compressor and to the supportive engine outer casing 28 without imparting a torsional load on the outlet guide vanes 22. The means comprises a plurality of loading bars 32 formed in the combustion chamber outer casing 30 which are angled relative to the applied axial load F.sub.A at the same angle as the chord line C of the outlet guide vanes 22 is angled relative to the engines center line C.sub.L. A significant proportion of the axial load F.sub.A is reacted along the load bars 32 and through the vanes 22 without importing twist into said vanes. The comparatively small torsional reaction load required is reacted through the inlet guide vanes 26 of the turbine 16.

REFERENCES:
patent: 3844115 (1974-10-01), Freid
patent: 4502276 (1985-03-01), Pask
patent: 4716721 (1988-01-01), Pask et al.

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