Ramjet combustor rectification grille

A technology of ramming combustion chamber and rectifying grille, which is applied in the field of aero-engines, can solve the problems of total pressure loss and performance impact of ramming combustion chamber, etc., achieve lower cost, improve the ability to reduce airflow unevenness, and ensure the effect of normal operation

Active Publication Date: 2020-12-22
AECC SICHUAN GAS TURBINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method generally requires the rectification grid to have a large blockage ratio in order to have a good rectification effect, but an excessive blockage ratio will cause a huge total pressure loss, which has a great impact on the performance of the ram combustion chamber

Method used

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  • Ramjet combustor rectification grille
  • Ramjet combustor rectification grille
  • Ramjet combustor rectification grille

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Embodiment Construction

[0024] Embodiments of the present disclosure will be described in detail below in conjunction with the accompanying drawings.

[0025] Embodiments of the present disclosure are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present disclosure from the contents disclosed in this specification. Apparently, the described embodiments are only some of the embodiments of the present disclosure, not all of them. The present disclosure can also be implemented or applied through different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present disclosure. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in the present disclosure, a...

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Abstract

The invention belongs to the technical field of aero-engines, and particularly relates to a ramjet combustor rectification grille. The ramjet combustor rectification grille comprises a front grille body and a rear grille body, the front grille body is arranged at a diffuser inlet of a ramjet combustor and used for buffering high-speed airflow of the diffuser inlet and guiding part of the bufferedhigh-speed airflow to a center area of a diffuser, and the rear grille body is arranged at a diffuser outlet of the ramjet combustor and used for buffering the air flow in the center area of the diffuser and evenly diffusing the buffered air flow in the center area of the diffuser outwards along the center area. According to the ramjet combustor rectification grille, through the design scheme thatthe front and rear rectification grille bodies are arranged at the inlet and outlet of the diffuser for combined rectification, the defects of an existing ramjet combustor rectification grille are overcome; and compared with a traditional single-layer grille, the rectification capacity of the ramjet combustor rectification grille can be obviously improved, the unevenness of distorted airflow is reduced, and the total pressure loss of the grille can be effectively reduced.

Description

technical field [0001] The invention belongs to the technical field of aero-engines, and in particular relates to a rectification grid of a stamped combustion chamber. Background technique [0002] Factors such as the interaction between the shock wave and the boundary layer in the inlet channel and the angle of attack of the aircraft will lead to flow separation and uneven distribution of the flow field at the inlet of the ram combustor. The uneven air flow at the inlet of the ram combustor will cause the oil-gas distribution inside the ram combustor to deviate from the oil-gas ratio that is conducive to efficient combustion, which will reduce the combustion efficiency and narrow the stable combustion range. The thermal protection of the combustion chamber brings difficulties; the flow separation at the inlet of the combustion chamber may cause combustion to occur upstream of the stabilizer, which will cause the phenomenon of "hanging fire" on the fuel injection rod and the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/16F23R3/02
CPCF23R3/16F23R3/02Y02T50/60
Inventor 何陈邓远灏康松张飞周雄姜军钟世林
Owner AECC SICHUAN GAS TURBINE RES INST
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