Jet engine having radial turbine blades and flow-directing turbine manifolds
OwnerMohammad F. Hamedaniinventor
Life of this patent
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Abstract
A jet aircraft engine having an improved turbine section with curved intake manifolds to direct combustion gasses from the engine's combustion chamber into the turbine housing on a chordal flow path through the turbine generally perpendicular to the turbine rotor's axis of rotation. The turbine rotor has a number of radially extending turbine blades for transmitting energy from the combustion gasses to shaft work to drive the engine's fan and compressor. Exhaust manifolds can also be provided, directing the flow of exhaust gasses from the turbine to the engine's intake, and having noise and emissions control capability.
Claims21
A jet engine comprising:
- (a) a compressor for receiving and compressing air;
- (b) a combustion chamber for receiving compressed air from said compressor, said combustion chamber comprising means for introducing fuel into said compressed air to form a mixture, and means for combusting said mixture to generate a flow of combustion gasses;
- (c) a turbine for recovering energy from the flow of combustion gasses, said turbine comprising at least one rotor rotatable about an axis of rotation;
- (d) means for directing at least a portion of the flow of combustion gasses from said combustion chamber through said turbine along a non-radial flowpath generally perpendicular to the axis of rotation of said rotor;
- and
- (e) a fan for generating thrust within a working fluid, said fan being coupled to a driveshaft driven by said turbine.
A turbine system for extracting energy from the combustion gasses exiting the combustion chamber of a jet engine and converting the energy to drive the compressor of the jet engine, said turbine system comprising:
- (a) a housing;
- (b) a turbine rotor mounted within said housing and rotational about an axis of rotation;
- (c) a plurality of blades extending generally radially from said turbine rotor;
- and
- (d) at least one intake manifold for receiving at least a portion of the combustion gasses exiting the combustion chamber and directing the fluid along a flow path into said housing generally perpendicular to the axis of rotation of said turbine rotor, wherein the turbine system is coupled to a fan of the jet engine.
A turbine and manifold system for a jet engine, said turbine and manifold system comprising:
- (a) a turbine rotor rotational about an axis of rotation;
- (b) a housing surrounding said turbine rotor;
- (c) an intake manifold for collecting combustion gasses from a combustion chamber of a jet engine and directing the combustion gasses into the housing along a flowpath transverse to and spaced from the axis of rotation of said rotor;
- and
- (d) an exhaust manifold for collecting spent combustion gasses from the housing and discharging the spent combustion gasses adjacent an intake of the jet engine.
A turbine for a jet engine, said turbine comprising:
- (a) a turbine rotor rotational about an axis of rotation;
- (b) a housing surrounding said turbine rotor and comprising at least one cutout section for exposing a portion of said turbine rotor to a flow of cooling air;
- and
- (c) at least one intake manifold for receiving combustion gasses and directing the combustion gasses along a flowpath transverse to and spaced from the axis of rotation of said rotor.
Dependencies are inferred from the claim text.