GB652991A - Gas turbine power plant - Google Patents

Abstract

652,991. Gas turbine plant. LYSHOLM, A. Jan. 16, 1948, No. 1433. Convention date, Feb. 28, 1947. [A Specification was laid open to inspection under Sect. 91 of the Acts, July 19, 1948] [Class 110(iii)] [Also in Group XII] In a gas-turbine power-plant comprising a compressor, a combustion chamber and an axial flow gas turbine which exhausts into a reheat combustion chamber through a diffluser, the increase in area of the diffuser is obtained substantially entirely by an increase in the diameter of the outer wall of said diffuser. The air compressed in the two-stage centrifugal compressor 61, 62 is divided into two parts by a wall 68. One part passes radially inwardly through an annular slot 69 whilst the other part passes between the walls 68, 70 to the burners 71. After expansion in the turbine 72 the gases are discharged through an annular diffuser 73, the increase in cross-sectional area of which is obtained substantially entirely by the gradual increase in diameter of the outer wall 74, into the reheat chamber 75. The inner wall of the diffuser has an elongation 77a extending into the chamber 75 which causes a zone of turbulence into which fuel is injected at 78. Air from the diffuser 73 may pass directly to atmosphere through a passage 81 and annular slot 82 in the jet nozzle 79. The reheat chamber 75 has additional openings 83 controlled by flaps 84 for control purposes. The turbine may drive a propeller or an additional compressor through gearing 86. To prevent boundary layer separation the diffuser is provided with guide vanes 85 and the equivalent cone angle of the diffuser is of the order of 10 degrees to 15 degrees. The invention may be applied to a plant in which the gases from the reheat chamber pass to another turbine. The Specification as open to inspection under Sect. 91 comprises also the subject matter of Specification 666,062. An arrangement in which an additional compressor which supplies air to a reheat chamber and is driven, by a turbine actuated by the exhaust gases from the compressor turbine is also described. The air inlet to this compressor is annularly arranged facing forwardly on the outside of the nacelle and the exhaust gases from the turbine pass through an inwardly facing outlet. If desired the inlet and outlet may be arranged to discharge through a plurality of openings. Adjustable guide vanes actuated by a speed governor may be provided at the inlet of the compressor. This subject-matter does not appear in the Specification as accepted.