GB726347A - Improvements in or relating to gas turbine engines or units - Google Patents

Abstract

726,347. Gas turbine plant; elastic-fluid turbines. DAVIDOVITCH, V. March 31, 1953 [April 3, 1952], No. 8830/53. Class 110 (3). In a gas turbine engine having a recuperative type heat exchanger of annular form, the engine parts are largely enclosed by the heat exchanger to reduce loss of heat by radiation from those parts. The plant in Fig. 1 comprises a centrifugal air compressor 1 and a turbine 6 mounted on a common shaft 2, an annular heat exchanger D and an annular combustion chamber B. Air from the compressor 1 passes through ducts 4 to an annular inlet header 5 of the heat exchanger D which comprises tubes 19 mounted in tube plates 8, 21 and disposed longitudinally in an annular space between walls 13, 14. The heated compressed air from the heat exchanger passes through a duct E to the annular combustion chamber B which includes a flame tube 17 and fuel injectors 20. The combustion gases act on the turbine rotor blades 7 and pass through the exhaust passages F, C and enter the heat exchanger through ports I in the inner wall 13 and after passing over the tubes 19 exhaust at K. The plant in Figs. 3 and 4 comprises a centrifugal air compressor 1 and a turbine 6 mounted on a common shaft 2, also an output turbine 28 mounted on a shaft 30, an annular recuperative type heat exchanger D and a combustion chamber B. Air from the compressor 1 passes through a duct 4 to the air inlet manifold L of the heat exchanger which comprises a bank of tubes 31 of arcuate form, the heated air discharging from the manifold M through the duct E to the combustion chamber B. The gases pass in series through the two turbines 6, 28 and the exhaust gases pass through ducts F, C to the hot gas inlet I of the heat exchanger and after passing across the tubes 31 exhaust at K to atmosphere. The turbine disc in Fig. 1 may be cooled by air passing through the tube 16.