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A gas turbine engine which comprises a rotary air compressor and a gas turbine, each with a rotor mounted on opposite ends of a rotor shaft, which is journalled in a housing positioned between the compressor and the turbine. The housing includes reduction gears. A combustion chamber is connected bet

A gas turbine engine which comprises a rotary air compressor and a gas turbine, each with a rotor mounted on opposite ends of a rotor shaft, which is journalled in a housing positioned between the compressor and the turbine. The housing includes reduction gears. A combustion chamber is connected between the outlet air duct of the compressor and the hot gas inlet duct of the turbine. The power output is controlled by varying the air inlet to the compressor by means of an axially moving throttle control which limits the air passage into the compressor, either alone or in conjunction with variable angle compressor inlet pre-whirl vanes. It is also controlled by a shroud which surrounds the nozzle blades of the turbine. The shroud can be moved axially to limit the cross-section of flow of hot gas to the turbine blades. Auxiliary blades are mounted on the back of the turbine rotor which serves to draw cool outside air into the space between the housing and the hot gas inlet duct of the turbine, and up along the back surface of the turbine rotor, and through a plurality of axial holes drilled through the hub of the turbine rotor, all of which helps to cool the critical parts of the engine. Improved construction of the turbine rotor and the compressor rotor involves assembling the unit from a plurality of separate pieces which serve to provide a combined radial and axial flow of gases around the rotor blades. The fuel supply is controlled to be a function of the flow of air into the combustion chamber.

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A gas turbine engine, comprising: a. a rotary air compressor, having a stator with an air inlet, a substantially circular outlet air duct, and a coMpressor rotor said compressor including an axial air inlet for said compressor comprising the annular space between an inner cylinder, coaxial with said

A gas turbine engine, comprising: a. a rotary air compressor, having a stator with an air inlet, a substantially circular outlet air duct, and a coMpressor rotor said compressor including an axial air inlet for said compressor comprising the annular space between an inner cylinder, coaxial with said rotor shaft, and an outer flared coaxial cylindrical wall, and including means to adjustably partially close off said annular opening; a′variable angle pre-whirl vanes in the inlet of said compressor; b. a gas turbine having a stator with a substantially circular hot gas inlet duct, a gas outlet and a turbine rotor and means to control the cross-section for flow of hot gases to said turbine rotor; c. a housing having a rotor shaft journalled in said housing, said compressor rotor mounted on a first end of said rotor shaft, and said turbine rotor mounted on the second end of said rotor shaft; d. substantially cylindrical combustion chamber means connecting the end of said compressor outlet air duct to the inlet end of said turbine hot gas inlet duct; e. a tubular extension of said housing in which is positioned the support bearing for said second end of said rotor shaft on which said turbine rotor is mounted; f. said circular hot gas inlet duct for supplying hot gas to the turbine inlet nozzles surrounding said tubular extension with an annular clearance therebetween; and g. auxiliary blade means on the back surface of said turbine rotor to draw cool outside air axially through said annular clearance, and radially along the back surface of said turbine rotor, and into said turbine nozzle along with said hot gases from said hot gas inlet duct; whereby said tubular extension, the turbine nozzle and said turbine rotor are cooled by said cool air flow.