A general-purpose engine that directly heats air to generate thrust

Abstract

The invention discloses a general engine that producing thrust by directly heating air. The general engine comprises a heat source reaction device, a heat transfer device and a heat exchange system, wherein the heat source reaction device is mounted at the start end of the heat transfer device, the stop end of the heat transfer device is connected with the heat exchange system, the engine directly utilizes heat produced by the heat source reaction device, the heat is transferred to an air inlet of the engine through the heat transfer device, an air flow is completely heated in a short time, and after heating, the air flow is subjected to expansion, cooling and acceleration before being discharged from the engine to produce thrust. Through the reasonable heat transfer and air shunt design, the air flow entering the engine is efficiently heated, and after being subjected to an expansion surface of 3-5 DEG C in an air runner, is discharged at an accelerated rate to obtain the thrust. The process is completed without combustion reaction; in contrast to the traditional method of supplying heat through combustion, the general engine adopts the direct heat supply method, thereby avoiding reduced engine efficiency due to affected combustion reaction, and providing an interface and carrier for the application of efficient new energy.

Description

technical field [0001] The invention belongs to the application field of aerospace engines, and in particular relates to a general-purpose engine which directly heats air to generate thrust. Background technique [0002] Engine is one of the core technologies of aerospace vehicles. [0003] The existing public technical literature "Aero-engine Core Engine Technology and Engine Development Spectrum Research" (University of Electronic Science and Technology, 2007, master's thesis), the article introduces the development status, laws, Develop technical approaches and comprehensively analyze the characteristics of foreign engine core machines. In the document "Development of Nuclear Aero-Engine" (Flying Missile, 2009, No. 4), the research progress in foreign countries since the 1940s in the field of nuclear-energy aero-engines was introduced, and the US nuclear energy propulsion project in aircraft was mainly discussed. research program. In the Chinese patent CN1O3527319A, "a...

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Problems solved by technology

In the Chinese patent CN1O3527319A, "a new type of engine" is disclosed, which effectively solves the defects of high fuel consumption and low efficiency of the turboshaft engine when it works at low speed

[0004] However, the engine described in the document "Aero-engine Core Technology and Engine Development Model Spectrum Research" and the patent "A New Type of Engine" has the following defects: the first, the existing aero-engine mainly utilizes the heat generated by combustion to heat the gas, resulting in The efficiency of its combustion reaction determines the performance of the engine

[0005] The U.S. nuclear energy propulsion scheme introduced in the document "Development of Nuclear Aeroengines" has the following deficiencies: first, the structure of the heat transfer system is too simple and conceptual, and it is difficult to ensure the efficient transfer of heat from the reaction heat source and heat the gas; second, there is no The design of the heat exchange system cannot guarantee that the gas can be heated, expanded, and generate thrust to the greatest extent

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