GB606526A - Improvements in or relating to means for supporting gas-turbine power-plants - Google Patents

Abstract

606,526. Gas turbine plant; compressors. BRITISH AEROPLANE CO., Ltd., OWNER, F. M., and HENSTRIDGE, A. G. Oct. 9, 1945, No. 26373. [Classes 110 (i) and 110 (iii)] A gas turbine plant of the kind in which a compressor, turbine and combustion equipment form a unitary structure and certain of said parts are supported from each end of an axial flow compressor is supported by a structure surrounding the axial flow compressor which is attached to the compressor by means allowing relative radial and axial movement of the compressor and the turbine is supported by a cantilever structure secured to said structure surrounding the compressor. A gas turbine power plant is supported from a mounting ring 26, which may be attached to an aircraft, by a structure 19 which comprises a truncated conical member 21 to which a pair of end pieces 22, 23 are secured, e.g. by welding. The depth of the structure is made considerable to increase its rigidity and is reinforced by longitudinal channel shaped members 27. The flange 24 of the end piece 22 is secured to the casing of the centrifugal compressor 10 on the front end of which the auxiliaries and auxiliary gear-box are mounted. The conical member 21 surrounds and supports the axial flow compressor 9. The support at the discharge end comprises a member 31 which allows axial but not radial movement of the compressor and at the intake end comprises an annular member 18 supported by pivoted links 32 attached to pins 34 which may slide radially relative to the mounting ring 26, thus allowing both axial and radial movement of the compressor. The turbine driving the compressors is supported by a cantilever structure 29 from the annular ring 18. The compressor comprises an axial flow compressor 9, followed by a two-stage centrifugal compressor 10. The combustion chambers 7 may be located between the channel-shaped beams 27.