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US20090241549 |
SUBSONIC AND STATIONARY RAMJET ENGINES
A ramjet engine ( 3, 4, 5 ), flying at Mach 3 has 64% efficiency, and at Mach 4 has 76% efficiency. Ramjet engines are currently only used for supersonic flight and have not been used as stationary...
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US20090241505 |
RE-HEAT COMBUSTOR FOR A GAS TURBINE ENGINE
A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second...
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US20090235638 |
VARIABLE AREA NOZZLE ASSISTED GAS TURBINE ENGINE RESTARTING
A turbofan engine starting system includes a core nacelle housing ( 12 ), a compressor ( 16 ) and a turbine ( 18 ). The core nacelle is disposed within a fan nacelle ( 34 ). The fan nacelle...
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US20090235643 |
VALVE SYSTEM FOR A GAS TURBINE ENGINE
A valve system intermediate a secondary flow path and a primary flow path to selectively communicate secondary airflow into the primary gas flow path and control airflow injected from a higher...
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US20090235642 |
VALVE SYSTEM FOR A GAS TURBINE ENGINE
A valve system intermediate a secondary flow path and a primary flow path to selectively communicate secondary airflow into the primary gas flow path and control airflow injected from a higher...
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US20090235641 |
T-Jet
The following is the design of a personal, strap-on the back flight device. It is my version of an air breathing jetpack; it is designed to give an individual pilot vertical take-off, horizontal...
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US20090217643 |
Gas discharge device for a vehicle engine
The present invention provides gas discharge technique useful on vehicle engines. The technique comprises an s-shaped duct having an ejector formed therein to mix hot exhaust gas with a relatively...
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US20090211221 |
Auxiliary propulsor for a variable cycle gas turbine engine
A core engine of a variable cycle gas turbine engine includes a low pressure spool for generating streams of bypass air and pressurized air, and a high pressure spool for further pressurizing the...
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US20090211222 |
Rear propulsor for a variable cycle gas turbine engine
A gas turbine propulsion system comprises a turbofan engine, a peripheral duct, an annular frame, an auxiliary turbine and an auxiliary fan. The turbofan engine is configured to produce bypass air...
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US20090188234 |
SHARED FLOW THERMAL MANAGEMENT SYSTEM
A thermal management system includes at least two of a multiple of heat exchangers arranged in an at least partial-series relationship.
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US20090158704 |
Gas Turbine Engine
Variation in the available mixing plane areas in an exhaust arrangement of a gas turbine engine enables alteration and configuration for better thermal cycle performance of that engine. A shaped...
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US20090000304 |
INTEGRATED SUPPORT AND MIXER FOR TURBO MACHINERY
A support and air mixer includes an inner annular member, an outer annular member shaped and positioned such that an annular air gap is formed between the inner annular member and the outer annular...
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US20080190096 |
FLUID MIXER WITH AN INTEGRAL FLUID CAPTURE DUCTS FORMING AUXILIARY SECONDARY CHUTES AT THE DISCHARGE END OF SAID DUCTS
A fluid mixer for mixing two fluid streams 40, 42 includes a set of main lobes 26 defining alternating primary and secondary main chutes 30, 32 , one or more auxiliary lobes 28 intermediate...
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US20080141656 |
BYPASS TURBOMACHINE WITH ARTIFICIAL VARIATION OF ITS THROAT SECTION
The invention relates to a bypass turbomachine comprising a gas turbine engine provided with a fan disposed on a longitudinal axis of the turbomachine, and an annular nacelle surrounding the engine...
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US20080115484 |
Mixer For Separate-Stream Nozzle
A mixer for a separate-stream turbojet nozzle, the mixer comprising along a longitudinal axis (X-X′) both a fastener shroud ( 10 ) for connecting said mixer to the exhaust casing of the nozzle,...
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US20080112798 |
Compound clearance control engine
A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from...
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US20080105488 |
ROTARY MOTION MIXER FOR A CONVERGING-STREAM NOZZLE OF A TURBOMACHINE
The invention relates to a mixer for a bypass turbomachine, the mixer comprising a member having a sinusoidal portion at its end defining inner lobes and outer lobes, each outer lobe comprising a...
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US20080105487 |
CURVED LOBE MIXER FOR A CONVERGING-STREAM NOZZLE FOR A TURBOMACHINE
The invention relates to a mixer for a bypass turbomachine, the mixer comprising a cylindrical member having a sinusoidal portion at its downstream end defining inner lobes and outer lobes...
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US20080098719 |
Aircraft propulsion systems
Disclosed are propulsion systems 30 providing reduced fuel burn, weight and cost. A single gas generator core 38 drives multiple bladed propulsion elements 36 with a power train 48. The...
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US20080093174 |
Tip Turbine Engine with a Heat Exchanger
A liquid-air heat exchanger extracts thermal energy from an engine lubricating fluid system. The liquid-air heat exchanger is located within a tailcone section and is in communication with a...
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US20080060344 |
EXHAUST DUCT AND TAIL CONE ATTACHMENT OF AIRCRAFT ENGINES
An annular exhaust duct of a gas turbine engine includes inner and outer cases co-axially disposed, and radially spaced apart by a plurality of airfoils radially extending therebetween. The outer...
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US20080060343 |
Asymmetric serrated nozzle for exhaust noise reduction
An exhaust nozzle for use in a gas turbine engine comprises a flow body for receiving exhaust gas from the turbine engine and includes a leading edge and a trailing edge. The leading edge connects...
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