Axisymmetric adjustable air inlet channel for Ma0-6+ wide-range precooling and stamping combined engine

An engine shaft, wide-range technology, applied in the direction of combined engines, ramjet engines, machines/engines, etc., can solve the problems of decreased capture flow capacity and inability to provide engines, and achieve the effect of changing the shrinkage ratio and flexibly adapting

Pending Publication Date: 2020-01-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

The performance of the traditional fixed-geometry inlet meets the expected requirements at the design point, but in the non-design point state, the shock wave at the head of the inlet will change g

Method used

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  • Axisymmetric adjustable air inlet channel for Ma0-6+ wide-range precooling and stamping combined engine
  • Axisymmetric adjustable air inlet channel for Ma0-6+ wide-range precooling and stamping combined engine
  • Axisymmetric adjustable air inlet channel for Ma0-6+ wide-range precooling and stamping combined engine

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Embodiment Construction

[0022] Specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to assist in a comprehensive understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.

[0023] It should be noted here that, in order to avoid obscuring the present invention due to unnecessary details, only the device structure and / or processing steps closely related to the solution according to the present invention are shown in the drawings, and the steps related to the present invention are omitted. Invent other details that don't really matter.

[0024] The invention discloses a Ma0-6+wide-range precooling+ramming combination engine with an axisymmetrically adjustable intake port. figure 1 ...

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Abstract

The invention discloses an axisymmetric adjustable air inlet channel for a Ma0-6+ wide-range precooling and stamping combined engine. Turbojet and dual-mode stamping dual channels mainly consist of afixed cowl profile, a front-and-back translation center cone and a flow splitting plate part, and are in an open state all the time within the Mach number range of Ma0-6+. As the incoming Mach numberrises, the center cone moves forwards to guarantee a wide-range internal shock-on-lip, and the flow coefficient of the air inlet channel is 1.0; the flow splitting plate is linked with the center coneto guarantee that the shrinkage ratios of the turbojet and stamping channels are both increased along with rise of the Mach number, and flow distribution of the two channels is adjusted according todemands. Under a high Mach number, the stamping channel can be transformed into a scramjet mode from a ramjet mode.

Description

technical field [0001] The invention belongs to the technical field of advanced intake and exhaust systems for aerospace vehicles, and in particular relates to an axisymmetrically adjustable intake port of a Ma0-6+ wide-range precooling+ramming combined engine. Background technique [0002] The intake port is an important component of the air-breathing engine, and its flow capture coefficient is one of its key performance parameters. The performance of the traditional fixed-geometry inlet meets the expected requirements at the design point, but in the non-design point state, the shock wave at the head of the inlet will change greatly, resulting in a significant decline in the capture flow capacity, so its performance in a wide Mach number Cannot always provide enough required flow to the engine when operating in range. In a wide-range pre-cooling + ram combination engine, the turbojet channel is in working condition under the action of the pre-cooler and the full working co...

Claims

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Application Information

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IPC IPC(8): F02C7/042F02C7/057F02K7/16
CPCF02C7/042F02C7/057F02K7/16
Inventor 金志光蔡伊雯田维康胡金源沈理
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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