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Turbine-based combined cycle engine, aircraft and control method

A turbine-based combination and turbine engine technology, applied in the aviation field, can solve problems such as hindering aircraft thrust, turbine engine thrust decline, and affecting the function of TBCC

Pending Publication Date: 2022-06-24
AERO ENGINE ACAD OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At this time, the thrust of the turbine engine has been seriously reduced, and the ramjet engine has not yet produced enough thrust, which affects the function of TBCC
In order to solve this problem, a preheater can be installed at the turbine channel, but the preheater hinders the thrust of the aircraft at low speed

Method used

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  • Turbine-based combined cycle engine, aircraft and control method
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Embodiment Construction

[0027] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention.

[0028] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

[0029] In addition, the terms "first" and "second" are only used for descriptive purposes, and should not be construed as indicating or implying relative importance or implying the number of indicated tech...

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Abstract

The invention discloses a turbine-based combined cycle engine, an aircraft and a control method, relates to the technical field of aviation, and aims to ensure that the turbine-based combined cycle engine provides enough thrust for the aircraft at various flight speeds. The turbine-based combined cycle engine comprises a turbine engine, a ramjet engine, a precooler, an air inlet pipe, an exhaust nozzle, a partition plate, a flow guide mechanism and a flow channel switching mechanism, wherein the partition plate, the flow guide mechanism and the flow channel switching mechanism are arranged in the air inlet pipe. The aircraft comprises the turbine-based combined cycle engine. The turbine-based combined cycle engine provided by the invention is used in an aircraft.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a turbine-based combined cycle engine, an aircraft and a control method. Background technique [0002] Currently, the Turbine Based Combined Cycle (TBCC) consists of a combination of a turbine engine and a ramjet, which can be used as a power system in hypersonic aircraft. Turbine engines work when a hypersonic aircraft is flying at low speeds, and ramjets work when a hypersonic aircraft is flying at high speeds. [0003] However, the flight speed range of conventional turbine engines is generally Ma0 to 2, and the flight speed range of conventional ramjet engines is generally Ma3.5 to 6. The inventors found that the turbo-based combined cycle (TBCC) engine had insufficient thrust (called a thrust trap) when the flight speed range was around Ma3. At this time, the thrust of the turbine engine has been severely reduced, and the ramjet engine has not yet been able to generate e...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K7/16F02C7/04F02C7/057
CPCF02K7/16F02C7/04F02C7/057
Inventor 苗辉周琨魏宽李亚忠
Owner AERO ENGINE ACAD OF CHINA
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