A support plate flame stabilizing device for a hydrogen-fueled subsonic ramjet engine

Abstract

This invention discloses a support plate flame stabilization device for a hydrogen-fueled subsonic combustion ramjet engine, comprising a support plate, multiple first nozzles, and multiple second nozzles. The support plate has a cavity for introducing hydrogen fuel. The support plate is radially distributed within the combustion chamber of the hydrogen-fueled subsonic combustion ramjet engine. The support plate, the multiple first nozzles, and the multiple second nozzles are connected as a single unit, with the height of the first nozzles greater than the height of the second nozzles. The multiple first nozzles are symmetrically arranged on both sides of the support plate, and the multiple second nozzles are symmetrically arranged on both sides of the support plate, with the first and second nozzles alternating in distribution. This invention, through the rational arrangement of the support plate angle and nozzle positions, and the combination of high and low nozzles, can increase the hydrogen fuel penetration depth, enhance the air-fuel mixing effect, and meet the requirements of the ramjet engine operating within a wide range of Ma2-Ma6, while ensuring high combustion efficiency, low resistance, enhanced mixing, and stable combustion.

Description

Technical Field

[0001] This invention relates to the fields of combined power, hydrogen fuel subsonic ramjet combustion chambers and ducted combustion chambers, and more specifically to a support plate flame stabilization device for a hydrogen fuel subsonic ramjet engine. Background Technology

[0002] Ramjet engines are highly efficient power units for spaceplanes, missiles, and other aircraft flying at high altitudes and speeds. Hydrogen's energy density is approximately three times that of standard aviation kerosene; hydrogen-fueled ramjet engines have a high specific impulse; hydrogen has excellent combustion performance, with a high flame propagation speed and high combustion efficiency; the combustion products of hydrogen and air have good expansion and working capabilities; hydrogen is also a fuel with a high heat sink, and among practical fuel gases, hydrogen fuel has the best thermal conductivity. Based on these characteristics, hydrogen is an ideal high-quality fuel for use in ramjet engines. Unlike traditional kerosene and air combustion, hydrogen and air undergo diffusion combustion in the subsonic ramjet combustion chamber. Enhancing the mixing of hydrogen and air to reduce flame length is the primary challenge faced by hydrogen-fueled subsonic ramjet combustion chambers.

[0003] Traditional hydrogen-fueled subsonic ramjet combustors suffer from hydrogen concentration issues due to the flame stabilizer, inevitably leading to poor combustion and reduced efficiency. Integrating the hydrogen nozzle and flame stabilizer into a single design can shorten the ramjet combustor length and reduce the weight of the ramjet engine.

[0004] For hydrogen fuel submerged ramjet combustion chambers, the mixing effect of fuel and air and the combustion efficiency are crucial. Different hydrogen fuel injection methods directly affect the mixing effect of hydrogen fuel and air, which in turn affects the combustion efficiency and combustion stability.

[0005] Therefore, providing a flame stabilizing device for hydrogen-fueled subsonic ramjet engines that offers high combustion efficiency, low resistance, enhanced mixing, and stable combustion, and meets a wide operating range, is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0006] In view of this, the present invention provides a support plate flame stabilizing device for a hydrogen fuel subsonic ramjet engine, which can increase the penetration depth of hydrogen fuel, enhance the mixing effect of air and fuel, meet the requirements of ramjet engine operation in the Ma2 to Ma6 range, and at the same time ensure high combustion efficiency, low resistance, enhanced mixing and stable combustion.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] A support plate flame stabilizing device for a hydrogen-fueled subsonic ramjet engine, comprising:

[0009] A support plate having a cavity for introducing hydrogen fuel; the support plate is radially distributed in the combustion chamber of the hydrogen fuel subsonic ramjet engine;

[0010] Multiple first nozzles and multiple second nozzles are provided, and the support plate, multiple first nozzles and multiple second nozzles are connected as one unit. The length of the first nozzle is greater than the length of the second nozzle. Multiple first nozzles are symmetrically arranged on both sides of the support plate, and multiple second nozzles are symmetrically arranged on both sides of the support plate, with the first nozzles and second nozzles alternating.

[0011] Furthermore, the support plate includes a front edge, a straight section, and a leeward surface connected sequentially from front to back, the front edge being a quadratic curved surface; the width of the straight section is 60mm; the width of the leeward surface is 22mm; the straight section, a plurality of first nozzles, and a plurality of second nozzles are connected as a whole, the plurality of first nozzles being symmetrically arranged on both sides of the straight section, and the plurality of second nozzles being symmetrically arranged on both sides of the straight section.

[0012] Furthermore, a gas pipeline connection pipe is fixedly connected to the bottom inner wall of the internal flow channel of the support plate.

[0013] Furthermore, the angle between the front edge of the support plate and the incoming flow is 110°.

[0014] Furthermore, multiple first nozzles located on the same side of the straight section are equally spaced along an oblique line with an angle of 110° to the incoming flow, and multiple second nozzles located on the same side of the straight section are equally spaced along an oblique line with an angle of 110° to the incoming flow; the angle between the multiple first nozzles and the straight section along the windward direction is 120°, and the angle between the multiple second nozzles and the straight section along the windward direction is 120°.

[0015] Furthermore, the first nozzle and the second nozzle have the same structure, both including a nozzle leading edge and a nozzle rear section connected as one piece. The nozzle leading edge is a quadratic curved surface; the nozzle rear section is a semi-circular surface with an aperture of 3.6-4.3mm.

[0016] Furthermore, the length of the first nozzle is 12mm, the length of the second nozzle is 6mm, and the straight-line distance between adjacent first and second nozzles is 16.5mm.

[0017] Furthermore, the blocking ratio of the flame stabilizing device is no greater than 0.25.

[0018] Therefore, the present invention provides a support plate flame stabilization device for a hydrogen fuel subsonic ramjet engine, which, compared with the prior art, produces the following beneficial effects:

[0019] 1) The use of adjacent high and low nozzles increases the hydrogen penetration depth and the mixing area of ​​hydrogen and air. Enhanced mixing is beneficial to strengthening combustion, thereby improving combustion efficiency.

[0020] 2) The shape and angle design of the support plate are conducive to airflow and have low flow resistance;

[0021] 3) The support plate adopts an integrated design, which reduces the number of parts. It can be processed by precision casting or 3D printing, with a short processing cycle and low production cost.

[0022] 4) Using hydrogen as fuel can achieve the goal of decarbonization and has promising application prospects. It can be used in annular ramjet combustion chambers or ducted combustion chambers. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0024] Figure 1 The attached figure is a schematic diagram of the overall appearance structure of a support plate flame stabilizing device for a hydrogen fuel subsonic ramjet engine provided by the present invention.

[0025] Figure 2 The attached figure is a side view of the overall appearance of a flame stabilizing device for a hydrogen fuel subsonic ramjet engine provided by the present invention.

[0026] Figure 3 The attached figure is a cross-sectional schematic diagram along the fuel internal flow channel of a support plate flame stabilizing device for a hydrogen fuel subsonic ramjet engine provided by the present invention.

[0027] Figure 4 The attached figure is a top cross-sectional view of a support plate flame stabilization device for a hydrogen fuel subsonic ramjet engine provided by the present invention.

[0028] Figure 5 The attached figure is a longitudinal cross-sectional view of the hydrogen nozzle of a support plate flame stabilization device for a hydrogen-fueled sub-steam ramjet engine provided by the present invention.

[0029] Figure 6 The attached figure is a cross-sectional view of the hydrogen nozzle of a support plate flame stabilization device for a hydrogen-fueled sub-steam ramjet engine provided by the present invention. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] like Figure 1-6 As shown in the figure, this invention discloses a support plate flame stabilization device for a hydrogen-fueled subsonic ramjet engine, comprising a support plate 1, multiple first nozzles 2, and multiple second nozzles 3. In this embodiment, the number of first nozzles 2 and second nozzles 3 are both 10-12. The support plate 1 has a cavity 9 for introducing hydrogen fuel. The support plate 1 is radially distributed in the combustion chamber of the hydrogen-fueled subsonic ramjet engine. The support plate 1, the multiple first nozzles 2, and the multiple second nozzles 3 are connected as a whole, and the length of the first nozzles 2 is greater than the length of the second nozzles 3. The multiple first nozzles 2 are symmetrically arranged on both sides of the support plate 1, and the multiple second nozzles 3 are symmetrically arranged on both sides of the support plate 1, with the first nozzles 2 and second nozzles 3 alternating. This invention, by reasonably arranging the angle of the support plate 1 and the nozzle positions, and by combining high and low nozzles, can increase the penetration depth of hydrogen fuel, enhance the mixing effect of air and fuel, meet the requirements of the ramjet engine operating in a wide range of Ma2-Ma6, and simultaneously ensure high combustion efficiency, low resistance, enhanced mixing, and stable combustion.

[0032] Specifically, the support plate 1 includes a front edge 4, a straight section 5, and a leeward surface 6 connected in sequence from front to back. The front edge 4 has a quadratic curved surface. The width of the straight section 5 is 60mm. The length of the leeward surface 6 is 22mm. The straight section 5, multiple first nozzles 2, and multiple second nozzles 3 are connected in one piece. The multiple first nozzles 2 are symmetrically arranged on both sides of the straight section 5, and the multiple second nozzles 3 are symmetrically arranged on both sides of the straight section 12.

[0033] Specifically, a gas pipeline connection pipe 8 is fixedly connected to the bottom inner wall of the internal flow channel of the support plate.

[0034] Specifically, the angle between the leading edge 4 and the incoming flow is 110°.

[0035] Specifically, multiple first nozzles 2 located on the same side of the straight section 5 are equally spaced along an oblique line with an angle of 110° to the incoming flow in front, and multiple second nozzles 3 located on the same side of the straight section 5 are equally spaced along an oblique line with an angle of 110° to the incoming flow in front; the angle between the multiple first nozzles 2 and the straight section 5 along the windward direction is 120°, and the angle between the multiple second nozzles 3 and the straight section 5 along the windward direction is 120°.

[0036] Specifically, the first nozzle 2 and the second nozzle 3 have the same structure, both including a nozzle leading edge and a nozzle rear section connected as one piece. The nozzle leading edge is a quadratic curved surface; the nozzle rear section is a semi-circular surface with an orifice diameter of 3.6-4.3mm.

[0037] Specifically, the length of the first nozzle 2 is 12mm, and the length of the second nozzle 3 is 6mm; the straight-line distance between adjacent first nozzle 2 and second nozzle 3 is 16.5mm.

[0038] Specifically, the blocking ratio of the flame stabilizing device is no greater than 0.25.

[0039] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0040] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A flame stabilizing device for a hydrogen-fueled subsonic ramjet engine, characterized in that, include: A support plate, the interior of which has a cavity for introducing hydrogen fuel; The support plates are radially distributed in the combustion chamber of the hydrogen fuel subsonic ramjet engine; Multiple first nozzles and multiple second nozzles are provided, and the support plate, multiple first nozzles and multiple second nozzles are connected as one unit. The height of the first nozzles is greater than the height of the second nozzles. Multiple first nozzles are symmetrically arranged on both sides of the support plate, and multiple second nozzles are symmetrically arranged on both sides of the support plate, with the first nozzles and second nozzles alternating in distribution. The support plate includes a front edge, a straight section, and a leeward surface connected sequentially from front to back. The front edge has a quadratic curved surface. The width of the straight section is 60 mm. The length of the leeward surface is 22 mm. The straight section, a plurality of first nozzles, and a plurality of second nozzles are connected as a whole. The plurality of first nozzles are symmetrically arranged on both sides of the straight section, and the plurality of second nozzles are symmetrically arranged on both sides of the straight section. Multiple first nozzles located on the same side of the straight section are equally spaced along an oblique line with an angle of 110° to the incoming flow. Multiple second nozzles located on the same side of the straight section are equally spaced along an oblique line with an angle of 110° to the incoming flow. The angle between the multiple first nozzles and the straight section along the windward direction is 120°. The angle between the multiple second nozzles and the straight section along the windward direction is 120°.

2. The flame stabilizing device for a hydrogen-fueled subsonic ramjet engine according to claim 1, characterized in that, A gas pipeline connection pipe is fixedly connected to the bottom inner wall of the internal flow channel of the support plate.

3. A flame stabilizing device for a hydrogen-fueled subsonic ramjet engine according to claim 2, characterized in that, The angle between the leading edge and the incoming flow is 110°.

4. A flame stabilizing device for a hydrogen-fueled subsonic ramjet engine according to claim 3, characterized in that, The first nozzle and the second nozzle have the same structure, both including a nozzle leading edge and a nozzle rear section connected as one piece. The nozzle leading edge is a quadratic curved surface; the nozzle rear section is a semi-circular surface with an aperture of 3.6-4.3mm.

5. A flame stabilizing device for a hydrogen-fueled subsonic ramjet engine according to claim 1, characterized in that, The height of the first nozzle is 12mm, and the height of the second nozzle is 6mm; The straight-line distance between the adjacent first nozzle and the second nozzle is 16.5 mm.

6. A flame stabilizing device for a hydrogen-fueled subsonic ramjet engine according to claim 1, characterized in that, The blocking ratio of the flame stabilizer is no greater than 0.25.

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