Electric turbine bypass fan and compressor for hybrid propulsion

a technology of bypass fan and compressor, which is applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve the problems of gas turbine engines, devices powered by gas turbine engines, and limited overall design and performance, so as to reduce the number of rotor/diffuser compressor stages

Inactive Publication Date: 2008-07-24
SONIC BLUE AEROSPACE
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Benefits of technology

[0014]Another object is to reduce the number of rotor / diffuser compressor stages.

Problems solved by technology

Gas turbine engines, and the devices that are powered by gas turbine engines, are limited in overall design and performance by mechanical, material, and thermodynamic laws.
They are further constricted by the design limitations of the three elements that make up the baseline design of gas turbine engines: the compressor, the combustor and the turbine.
Typically, selection of rotational speed is complex in current turbomachinary designs using drive shafts.

Method used

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  • Electric turbine bypass fan and compressor for hybrid propulsion
  • Electric turbine bypass fan and compressor for hybrid propulsion
  • Electric turbine bypass fan and compressor for hybrid propulsion

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Embodiment Construction

[0034]For the purposes of promoting an understanding of the principles of the invention, reference will now be made to the embodiments of the present invention illustrated in the drawing figures briefly described above. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended, such alterations and further modifications in the illustrated device, and such further applications of the principles of the invention as illustrated therein being contemplated as would normally occur to one skilled in the art to which the invention relates.

[0035]The key operations of the electric by-pass fan and electric turbocompressor-compounding compressor turbine system are that they are disengaged or engaged electrically, so that combustion cycles, compressor ratios, compressor cooling, thrust, and electric generation can be arranged and optimized for high thermodynamic and combustion efficiencies across the entire flight envelope, regardless of altitude, ai...

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Abstract

An electric turbine compressor fan for hybrid propulsion wherein the compressor contains one or more rotor stages (compressor and diffuser), each being driven by one or more electric ring motors, such that the compressor rotor stages are designed and tuned more precisely to the compression ratio to be attained within the turbine design operating characeristics, thrust requirements and flight envelope.

Description

FIELD OF THE INVENTION[0001]The invention relates to an electric turbine bypass fan and compressor for hybrid propulsion.BACKGROUND OF THE INVENTION[0002]Optimization of thermal power in turbine engines starts with the optimization of the thermodynamic cycle scheme, i.e. the thermodynamic relations of cycle media in the process of power production. In accordance with Carnot's Rule of Thermodynamics, it involves the introduction of fuel heat input at maximum possible temperature, compression and expansion, at maximum compressor and turbine efficiency, along with the release of non-convertible heat to ambient temperature at minimum loss.[0003]Gas turbine engines, and the devices that are powered by gas turbine engines, are limited in overall design and performance by mechanical, material, and thermodynamic laws. They are further constricted by the design limitations of the three elements that make up the baseline design of gas turbine engines: the compressor, the combustor and the tur...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D1/02
CPCF02C7/36
Inventor LUGG, RICHARD H.
Owner SONIC BLUE AEROSPACE
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