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A scramjet combustion chamber support plate with right-angled triangular grooves

A right-angled triangle and scramming technology, which is applied in combustion chambers, continuous combustion chambers, combustion methods, etc., can solve the problems of poor fuel/oxidant mixing effect and poor fuel atomization performance, and achieve the promotion of fuel/oxidant mixing, high heat Load capacity, effect of improving spanwise distribution

Active Publication Date: 2019-04-09
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is: the traditional trailing edge spraying branch plate has problems such as poor fuel atomization performance, concentrated distribution of fuel along the span direction, poor mixing effect of fuel / oxidant, etc.

Method used

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  • A scramjet combustion chamber support plate with right-angled triangular grooves
  • A scramjet combustion chamber support plate with right-angled triangular grooves
  • A scramjet combustion chamber support plate with right-angled triangular grooves

Examples

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Effect test

Embodiment 1

[0024] According to an embodiment of the present invention, for the traditional trailing edge spray strut (such as figure 1 shown) to improve the design (such as figure 2 shown). Compared with the traditional trailing edge spray support plate, the two sides of the support plate with right-angled triangular grooves have symmetrically arranged right-angled triangular groove structures 7, and the fuel injector 3 moves forward from the trailing edge to the top surface of the triangular groove 5 , the direction of the side edge 6 of the triangular groove and the direction 13 of fuel injection are parallel to the direction 12 of the airflow behind the front edge of the strut.

[0025] image 3 The working process of the support plate with right triangle groove is shown. Compared with the traditional trailing edge spraying branch plate, the branch plate arranges the fuel flow channel 4 at the sharp edge of the support plate, and the distance between the fuel 9 and the front edge ...

Embodiment 2

[0028] According to another embodiment of the present invention, the support plate with right-angled triangular groove (such as figure 2 Shown) further modified to achieve better results. Since the strength of the flow direction vortex 8 depends on the normal velocity difference of two adjacent airflows at the right angle junction 11 between the right triangle groove and the support plate, the symmetrically arranged right triangle grooves 7 on both sides of the support plate can be changed to staggered arrangement, and increase the normal depth of the right triangle groove 7 on the support plate, thereby improving the strength of the flow direction vortex 8. Compared with Embodiment 1, this modification introduces a stronger flow direction vortex, which can further improve the atomization performance of fuel and the mixing performance of fuel / oxidizer.

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Abstract

The invention provides a scramjet combustor supporting plate with right-angled triangular prism grooves. Compared with a traditional trailing edge downstream spray supporting plate, the scramjet combustor supporting plate is provided with the right-angled triangular prism groove structures, fuel injectors move forwards to the top faces of the right-angled triangular prism grooves from the trailing edge, and the direction of side edges of the right-angled triangular prism grooves and the fuel injection direction are parallel to the leading edge back airflow direction of the supporting plate. The supporting plate has the advantage that downstream spray has few losses compared with transverse spray; by arranging the fuel injectors on the front portion, the problem that downstream spray of fuel is short in atomization, evaporation and mixing time is solved; by fully utilizing streamwise vortexes generated at the right-angled junctions of the triangular prism grooves and the supporting plate, the fuel atomization performance and the fuel and oxidizing agent mixing performance are improved at a low flow loss cost; by fully utilizing the spanwise vortexes at the trailing edge of the supporting plate are fully utilized, mixing of fuel and an oxidizing agent is further prompted, and distribution of fuel in the spanwise direction is improved; and a fuel runner is distributed at the leading edge of the supporting plate, so that the thermal load capacity of the supporting plate is effectively improved.

Description

technical field [0001] The invention relates to the technical field of scramjet combustor, TBCC and RBCC combined power combustor, in particular to a support plate based on flow direction vortex mixing enhancement technology, the support plate has better fuel atomization performance and fuel / oxidizer mixing Performance and span-wise distribution of fuel. Background technique [0002] When the aircraft flies at hypersonic speed in the atmosphere, the scramjet has a greater advantage than the rocket propulsion system due to its large specific impulse and high Mach number cruise. In combined power systems such as TBCC (Turine-based combined cycle) or RBCC (Rocket-Based Combined Cycle), the combination of scramjet engine and turbine engine or rocket propulsion system can more effectively expand the flight boundary of the aircraft, and is expected to As the most promising power system, it has been highly valued by various countries. [0003] The fuel injection technology of scr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/28
CPCF23R3/28
Inventor 刘玉英刘广海
Owner BEIHANG UNIV
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