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Encircling-type double-duct variable-cycle engine and control method

A variable-cycle engine and engine technology, which is applied to machines/engines, jet propulsion devices, etc., can solve problems such as difficulty in meeting low-cost use needs, difficulty in design and manufacturing, and increasing the cost of engine manufacturing, so as to improve the infrared Stealth, improved efficiency, reduced fuel consumption

Pending Publication Date: 2022-01-28
太仓点石航空动力有限公司
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  • Description
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Problems solved by technology

[0003] However, most of the adjustable mechanisms are complex in structure, difficult to design and manufacture
The more and more stages of

Method used

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  • Encircling-type double-duct variable-cycle engine and control method
  • Encircling-type double-duct variable-cycle engine and control method
  • Encircling-type double-duct variable-cycle engine and control method

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[0043] Next, the technical solutions in the embodiments of the present invention will be described in connection with the drawings of the embodiments of the present invention, and it is understood that the described embodiments are merely the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually illustrative only, and it is not necessary to use any limitation of the invention and its application or use. Based on the embodiments in the present invention, all other embodiments obtained without creative labor are not made in the premise of creative labor. The components and steps set forth in these examples are arranged relatively arrangements unless otherwise specified. Expression and numerical values ​​do not limit the scope of the invention. At the same time, it should be understood that in order to facilitate the description, the dimensions of the respective portions shown in the drawings are n...

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Abstract

The invention discloses an encircling-type double-duct variable-cycle engine and a control method. The engine comprises an inner duct and an outer duct; the outer duct and the inner duct adopt a common air intake and exhaust device, and the common air intake and exhaust device comprises an adjustable air intake center cone, an adjustable exhaust tail cone, an adjusting channel and an adjusting flow; the device also comprises an outer duct support plate and an inner duct support plate which are used for rectifying and supporting to ensure that the air outlet direction of the air flow is backward in the axial direction without the speed perpendicular to the radial direction; a high-pressure contra-rotating turbine which forms a high-pressure rotor, a low-pressure contra-rotating gas compressor and a high-pressure barrel shaft keep the same rotating speed; and a low-pressure contra-rotating turbine which forms a low-pressure rotor, a low-pressure contra-rotating compressor, a fan and a low-pressure barrel shaft keep the same rotating speed. The two ducts share the air inlet and exhaust device, the adjustable air inlet center cone and the adjustable exhaust tail cone are used for adjusting the channels and adjusting the flow of the inner channel and the flow of the outer channel, then the working modes are changed and switched, and the requirements of high-speed flight and efficient flight are met.

Description

technical field [0001] The invention relates to a ring-wrapped double-duct variable-cycle engine, which belongs to the field of advanced variable-cycle aeroengine design. Background technique [0002] With the rapid development of aviation technology, higher requirements are put forward for the performance of aircraft, and multi-purpose, high range and all-weather with economical affordability have become a new development direction. In order to meet the dual performance requirements of high unit thrust and low cruising fuel consumption of the next-generation aircraft, it is an inevitable trend to develop adaptive variable cycle turbofan engines. Compared with the conventional aviation turbofan engine, the variable cycle engine has added a new bypass and corresponding variable geometry parts, which has obtained a wider adjustment range of the engine bypass ratio, taking into account the lower fuel consumption rate and supersonic speed in the subsonic state. The flight deman...

Claims

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Application Information

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IPC IPC(8): F02K3/04F02K1/06
CPCF02K3/04F02K1/06Y02T10/12Y02T50/60
Inventor 赵运生丁建国代钰程青青陶冶科
Owner 太仓点石航空动力有限公司
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