Ejector-assistant turbine-based combined cycle engine

A turbo-ramjet combination and turbine engine technology, which is applied in the direction of combined engines, ramjet engines, mechanical equipment, etc., can solve problems such as inability to transfer stages, small specific impulse, and high take-off fuel consumption

Inactive Publication Date: 2015-12-16
TSINGHUA UNIV
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Problems solved by technology

[0004] The purpose of the present invention is to provide an ejection-assisted turbo-ram-press combined cycle engine, which uses a turbine to replace the rocket booster, in view of the bottleneck problem that the specific impulse in the rocket ram-press combination is relatively small and the turbo-ram-press combinat

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  • Ejector-assistant turbine-based combined cycle engine
  • Ejector-assistant turbine-based combined cycle engine
  • Ejector-assistant turbine-based combined cycle engine

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[0015] The structure, principle and working process of the present invention will be described in further detail below in conjunction with the accompanying drawings.

[0016] Such as Figure 1 ~ Figure 4 As shown, the ejection-assisted turbo ramjet combined cycle engine (E-TBCC engine) of the present invention is based on the integration of the engine and the aircraft, and the wall ejection rocket 19 or the support plate ejection rocket 24 is combined with the dual-mode superburning The ramjet 16 is integrated, and the wall ejection or support plate ejection is used to solve the problem of insufficient thrust faced when the turbine engine mode is converted to the ramjet mode. The combined cycle engine is mainly composed of a turbo engine (turbojet or turbofan engine) 7, a dual-mode scramjet 16, a plurality of side-by-side wall ejection rockets 19 and a plurality of side-by-side grooves (or multiple The side-by-side support plates eject the rocket and multiple side-by-side suppor...

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Abstract

The invention discloses an ejector-assistant turbine-based combined cycle engine, and relates to a reusable combined cycle engine applied to aircrafts and spacecrafts. The engine mainly consists of a turbine engine, rocket ejectors and a dual-mode scramjet engine, wherein the turbine engine and the scramjet engine work in parallel, and the rocket ejectors and the scramjet engine are in integrally designed. When the engine is converted from a turbine engine mode to a scramjet engine mode, ejection fuel-gas streams are ejected into the scramjet engine from support plates or side walls of the scramjet engine; inlet air of the scramjet engine is mixed with the ejection fuel-gas streams, and afterburning is performed. The fuel gas ejected by the rocket ejectors can overcome the defect that thrust is not enough when the turbine engine mode is converted into the scramjet engine mode, so that the combined engine disclosed by the invention can has the advantage of smooth transition during mode conversion.

Description

technical field [0001] The patent of the present invention relates to a novel combined engine, in particular to a reusable Ejector-Assistant Turbine-Based Combined Cycle (Ejector-Assistant Turbine-Based Combined Cycle, referred to as E-TBCC) engine applied to aerospace vehicles. Background technique [0002] Combination engine is an important development direction of aerospace integrated weapon system in the future, and it will also be the main power form of next-generation aerospace vehicles. At present, combined engines include two categories: turbine-based combined cycle engines (Turbine Based Combined Cycle, hereinafter referred to as TBCC) and rocket-based combined cycle engines (Rocket Based Combined Cycle, hereinafter referred to as RBCC). The TBCC power system is an air-breathing engine that is organically combined with a turbojet (or turbofan) engine and a ramjet; RBCC is a combined cycle system that organically combines a rocket and a dual-mode ramjet. With the in...

Claims

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Application Information

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IPC IPC(8): F02K7/16
Inventor 侯凌云梁新刚张扬军周兵
Owner TSINGHUA UNIV
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