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Regenerative cycle engine

A regenerative cycle, engine technology, used in aviation, to solve problems such as pressure loss, heavy structure and weight

Inactive Publication Date: 2021-04-23
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the process of leading the engine core flow to the intercooler or regenerator not only has to pay a heavy structural and weight cost, but also causes a large pressure loss, which will eventually offset the effect of the intercooler and heat recovery cycle. income

Method used

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  • Regenerative cycle engine

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Embodiment Construction

[0022] The regenerative cycle engine of the present invention is further described below in conjunction with the accompanying drawings:

[0023] The engine includes: the last stage vane (1) of the compressor, a booster pump (2), a liquid outlet pipe (3), a cooling interlayer (4), a spray pipe (5), a liquid return pipe (6), a return pipe Liquid pump (7), combustion chamber (8); the regenerative cycle engine of the present invention is provided with cooling interlayer outside the nozzle, and the last stage stator vane of the compressor communicates with the cooling interlayer by a liquid outlet pipe and a liquid return pipe. The first-stage vane, cooling interlayer, liquid outlet pipe and liquid return pipe are filled with bismuth-lead alloy liquid metal. A booster pump is arranged on the liquid outlet pipe, and a liquid return pump is arranged on the liquid return pipe to drive the bismuth-lead alloy liquid metal to flow along the pipeline. The high-temperature jet in the nozz...

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PUM

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Abstract

The invention provides a regenerative cycle engine. The regenerative cycle engine comprises a last-stage stationary blade (1) of a gas compressor, a booster pump (2), a liquid outlet pipe (3), a cooling interlayer (4), a spray pipe (5), a liquid return pipe (6), a liquid return pump (7) and a combustion chamber (8), wherein the liquid outlet pipe (3) is of a tubular structure, the booster pump (2) is arranged on the liquid outlet pipe (3), an inlet of the liquid outlet pipe (3) communicates with the upper side of the last-stage stationary blade (1) of the gas compressor, and an outlet of the liquid outlet pipe (3) communicates with an inlet of the cooling interlayer (4); the liquid return pipe (6) is of a tubular structure, the liquid return pump (7) is arranged on the cooling interlayer (4), an inlet of the liquid return pipe (6) communicates with an outlet of the cooling interlayer (4), and an outlet of the liquid return pipe (6) communicates with the lower side of the last-stage stationary blade (1) of the gas compressor; and the cooling interlayer (4) is of a cylindrical interlayer structure, and the cooling interlayer (4) is located on the outer side of the spray pipe (5).

Description

technical field [0001] The invention belongs to the field of aviation and relates to a regenerative cycle engine. Background technique [0002] The improvement of the thermal efficiency of the engine is mainly realized by innovating the thermodynamic cycle or breaking through the technology of major components. The intercooling and regenerating cycle engine is a kind of innovative thermodynamic cycle. The working principle of the disclosed intercooling heat recovery cycle engine is usually: (1) intercooling link, the intercooler is located in the external duct of the engine, and the engine fan outlet or the airflow of the compressor intermediate stage is led to the intercooler through the pipeline, Heat exchange with the outside atmosphere to reduce the compression work; (2) The heat recovery link, the regenerator is located in the nozzle, and the inlet airflow of the combustion chamber is led to the regenerator through the pipeline to exchange heat with the airflow in the n...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/08F02K1/82
CPCF02C7/08F02K1/822F02K1/825
Inventor 周红秦浩吴宇
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA