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Hybrid flight vehicle

A technology for hybrid power and aircraft, which is used in aircraft, aircraft power units, gas turbine power units, etc.

Active Publication Date: 2020-05-22
HONDA MOTOR CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical configuration described in Patent Document 1 is to extract high-pressure gas (energy) generated in a gas turbine engine by rotating it through a turbine, and drive the rotor, or to drive the rotor with electricity obtained by driving a generator. As the rotation of the turbine, the extraction is exhausted, leaving a problem in terms of thermal efficiency.

Method used

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no. 2 Embodiment approach

[0066] Figure 13 It schematically shows the hybrid aircraft of the second embodiment of the present invention, and figure 2 An explanatory cross-sectional view of the same GT16 etc.

[0067] Focusing on the difference from the first embodiment, in the second embodiment, a turbine 26 b driven by exhaust gas discharged from the GT 16 is used as the second turbine 26. The turbine 26b is configured independently of the drive system of the generator 20, and includes a turbine that is driven by exhaust gas introduced from the downstream of the turbine 16b of the GT 16 through the introduction passage 16b2 and can drive the rotor 14 and the like.

[0068] The second embodiment is configured as described above. Therefore, in the hybrid aircraft 10 having a plurality of rotors 14 driven by GT16 or electric driven by a generator 20 driven by GT16, there is a second turbine 26 provided independently of GT16. (Turbine 26b) Therefore, the thermal efficiency of the high-pressure gas generated...

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Abstract

The invention provides a hybrid flight vehicle, having four rotors (14) configured to produce thrust to propel a frame, a gas turbine engine (GT, 16) incorporating a compressor (16a) and a first turbine (16b) adapted to rotate integrally with the compressor, a generator (20) connected to the output shaft of the GT and configured to generate electric power, a battery (22) configured to store powergenerated by the generator, four motor-generators (M / G, 24) connected to the battery and the multiple rotors to drive the rotors when power is supplied from the battery, while generating power when driven by the rotors. In the vehicle, there is provided a second turbine(26) provided independently of the gas turbine engine and configured to drive the rotors when supplied high pressure gas outputted from the gas turbine engine.

Description

Technical field [0001] The invention relates to a hybrid power aircraft, in particular to a plurality of rotors driven by electricity generated by a generator, the generator being driven by a gas turbine engine or a gas turbine engine. Background technique [0002] As a hybrid aircraft as described above, the technology described in Patent Document 1 is known. In the technology described in Patent Document 1, the high-pressure gas generated in the gas turbine engine is rotated by a turbine and extracted, and the rotor is directly driven based on the extracted rotation, or based on the electricity obtained by driving the generator by the extracted rotation. Drive the rotor. [0003] The technology described in Patent Document 1 is configured to extract high-pressure gas (energy) generated in a gas turbine engine in a rotating manner through a turbine to drive a rotor, or an electric drive obtained by driving a generator, but the high-pressure gas is removed In addition to the extr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/02B64D31/00B64C29/00
CPCB64D27/02B64D31/00B64C29/0083B64D27/026B64D35/08B64D27/24B64D27/10Y02T50/60B64C29/0025B64D31/18B64C27/32B64C27/14
Inventor 玉田俊一郎
Owner HONDA MOTOR CO LTD