Gas turbine engine
First Claim
1. In a gas turbine engine intended for aircraft propulsion and having front and rear ends defined in relation to the direction of travel of the aircraft propelled by said engine,an engine casing,air intake means including a plurality of inlet ducts arranged around said engine casing,means defining an annular chamber disposed to receive said intake air from said inlet ducts,a gas generator disposed to receive said intake air from said annular chamber and comprisingcompression stages,a combustion chamber, andturbine stages for driving said compression stages, said annular chamber being located to the rear of said gas generator and said generator being arranged such that said air from said chamber travels in a forward direction successively through said compression stages, said combustion chamber, and said turbine stages of said gas generator,a forwardly extending axial outlet duct from said gas generator,two interdigitated, contra-rotating, low-speed power turbines adapted to be driven by hot gases from said gas generator and disposed in a radially superposed relationship outwards of said axial outlet duct,means connected to said axial outlet duct for receiving said gases from said gas generator and reversing the direction of flow thereof to feed said gases in a rearward direction through said power turbines, andejection means for said gases exiting from said power turbines,wherein the interior disposition of said engine, from front to rear, comprises in succession:
- said interdigital, contra-rotating, power turbines and said axial outlet duct from said gas generator in radial superposition;
said turbine stages of said gas generator;
said combustion chamber;
said compression stages of said gas generator, andsaid annular air inlet chamber.
1 Assignment
0 Petitions
Accused Products
Abstract
A gas turbine engine for an aircraft comprises a gas generator which includes a compressor stage, a combustion chamber, and a turbine for driving the compressor, and through which the air and combustion gases flow from the rear towards the front in relation to the direction of travel of the aircraft before undergoing a reversal of direction to feed two contra-rotating power turbines which directly drive two contra-rotating airscrew or fan stages located near the front of the engine in the same longitudinal region as the power turbines. The gas generator is supplied by an air intake consisting of a plurality of ducts disposed around the outer casing of the engine, and the gases exiting from the power turbines are exhausted through a plurality of ducts positioned between the inlet ducts.
36 Citations
8 Claims
-
1. In a gas turbine engine intended for aircraft propulsion and having front and rear ends defined in relation to the direction of travel of the aircraft propelled by said engine,
an engine casing, air intake means including a plurality of inlet ducts arranged around said engine casing, means defining an annular chamber disposed to receive said intake air from said inlet ducts, a gas generator disposed to receive said intake air from said annular chamber and comprising compression stages, a combustion chamber, and turbine stages for driving said compression stages, said annular chamber being located to the rear of said gas generator and said generator being arranged such that said air from said chamber travels in a forward direction successively through said compression stages, said combustion chamber, and said turbine stages of said gas generator, a forwardly extending axial outlet duct from said gas generator, two interdigitated, contra-rotating, low-speed power turbines adapted to be driven by hot gases from said gas generator and disposed in a radially superposed relationship outwards of said axial outlet duct, means connected to said axial outlet duct for receiving said gases from said gas generator and reversing the direction of flow thereof to feed said gases in a rearward direction through said power turbines, and ejection means for said gases exiting from said power turbines, wherein the interior disposition of said engine, from front to rear, comprises in succession: -
said interdigital, contra-rotating, power turbines and said axial outlet duct from said gas generator in radial superposition; said turbine stages of said gas generator; said combustion chamber; said compression stages of said gas generator, and said annular air inlet chamber. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
-
Specification