CN115355533B

CN115355533B - Hydrogen fuel combustion chamber head structure of runway type jet hole

Info

Publication number: CN115355533B
Application number: CN202210969323.6A
Authority: CN
Inventors: 莫妲; 刘一雄
Original assignee: AECC Shenyang Engine Research Institute
Current assignee: AECC Shenyang Engine Research Institute
Priority date: 2022-08-12
Filing date: 2022-08-12
Publication date: 2023-06-20
Anticipated expiration: 2042-08-12
Also published as: CN115355533A

Abstract

The application provides a hydrogen fuel combustion chamber head structure of runway formula jet hole belongs to aeroengine structural design technical field, and this hydrogen fuel combustion chamber head structure includes: the air inlet end face is arranged on one side of the air guide disc, the air outlet end face is arranged on the other side of the air guide disc, and at least one annular mixing groove is arranged on the air outlet end face of the air guide disc; the two radial sides of the mixing groove form a hydrogen guide plate; a non-penetrating hydrogen injection channel extending along the axis is arranged on the hydrogen guide plate from the air inlet end face to the air outlet end face, a plurality of circumferentially distributed and radially extending hydrogen jet holes are arranged at the tail end of the hydrogen injection channel close to the air outlet end face, and the hydrogen jet holes are communicated with the mixing groove and the hydrogen injection channel; the air jet holes penetrate through two sides of the flow guide disc and are communicated with the air inlet end face and the mixing groove.

Description

Hydrogen fuel combustion chamber head structure of runway type jet hole

Technical Field

The application belongs to the technical field of gas turbine design, and particularly relates to a hydrogen fuel combustion chamber head structure of a runway type jet hole.

Background

In the traditional aviation engine combustion chamber adopting aviation kerosene, the carbon content in aviation kerosene molecules is large, the carbon emission of the combustion chamber is relatively large, and decarburization emission cannot be realized. Although a low NOx emission combustion organization mode can be adopted, high-efficiency combustion cannot be realized in a short axial distance due to low aviation kerosene combustion rate, so that a large amount of cooling air is needed by a combustion chamber, and NOx in a main combustion area is difficult to reduce through lean oil design. Meanwhile, the axial size of the combustion chamber is long, so that the residence time of the fuel gas is prolonged, the emission of NOx is forced to be increased, and the weight of the combustion chamber is large.

The hydrogen fuel has the advantages of components, and when the hydrogen is combusted, the product is water or water vapor, so that zero carbon emission can be thoroughly realized. Compared with aviation kerosene, the stable combustion range of hydrogen is wider, and the stable combustion range can be combusted under the condition of insufficient mixing with air, so that the stable working boundary of the engine is greatly widened. Meanwhile, the fuel calorific value of the hydrogen is about 3 times that of aviation kerosene, and when the same air quantity is consumed, the required hydrogen is obviously reduced.

Therefore, the replacement of aviation kerosene by hydrogen fuel has wide prospect. For this reason, there is a need for a new configuration of combustion chamber head structure that can achieve hydrogen fuel combustion, determining combustion organization, combustion efficiency and pollutant emissions.

Disclosure of Invention

It is an object of the present application to provide a hydrogen fuel combustion chamber head structure of a racetrack jet hole to address or mitigate at least one problem in the background art.

The technical scheme of the application is as follows: a hydrogen fuel combustion chamber head structure of a racetrack jet hole, comprising:

the air inlet end face is arranged on one side of the air guide disc, the air outlet end face is arranged on the other side of the air guide disc, and at least one annular mixing groove is arranged on the air outlet end face of the air guide disc;

the two radial sides of the mixing groove form a hydrogen guide plate;

a non-penetrating hydrogen injection channel extending along the axis is arranged on the hydrogen guide plate from the air inlet end face to the air outlet end face, a plurality of circumferentially distributed and radially extending hydrogen jet holes are arranged at the tail end of the hydrogen injection channel close to the air outlet end face, and the hydrogen jet holes are communicated with the mixing groove and the hydrogen injection channel;

the air jet holes penetrate through two sides of the flow guide plate and are communicated with the air inlet end face and the mixing groove, wherein the air jet holes are in a runway shape, and the runway shape is formed by two semicircles and a rectangle between the semicircles.

Further, the number of the mixing tanks is two or more.

Further, the number of the hydrogen guide support plates is one, and N is the number of the mixing grooves.

Further, the number of the hydrogen jet holes arranged on the side wall surface of the mixing groove is the same.

Further, the width of the air jet hole is larger than the diameter of the hydrogen jet hole, and the air jet hole is spaced from the side wall of the mixing groove.

Further, the center of the air jet hole is positioned on the circular ring of the radial width center line of the mixing groove, and the length direction of the air jet hole points to the center of the guide disc.

Further, the air jet holes distributed on the radial width central line circular ring with different mixing groove diameters have different pitches.

Further, the hydrogen fuel combustion chamber head structure is processed into an integral structure through an additive manufacturing mode.

The hydrogen fuel combustion chamber head structure of the runway type jet hole provided by the application enables air and hydrogen to be well mixed, flame scale to be small, flame temperature to be low and NOx emission to be remarkably reduced by forming a non-premixed lean oil combustion organization mode of multi-jet layout. Meanwhile, as the combustion matter is hydrogen, the emission of carbon dioxide is zero, and the combustion is extremely low in pollution. In addition, because the hydrogen combustion rate is fast, can high-efficient burning in the short range, flame dwell time is short, the size in the axial direction of the combustion chamber with this combustion chamber head structure can be shortened by a wide margin to can reduce combustion chamber weight, reduce the flight fuel consumption of engine, based on the wide suitable combustion characteristics of hydrogen, can widen the lean extinction boundary of combustion chamber, realize the wider working range of engine.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.

FIG. 1 is a schematic cross-sectional view of a hydrogen fuel combustion chamber head of the present application.

Fig. 2 is a view angle diagram based on the P-direction in fig. 1.

Reference numerals:

10-flow guiding disk

11-air inlet end face

12-exhaust end face

13-air jet holes

14-Hydrogen injection channel

15-Hydrogen jet hole

16-blending tank

17-center channel

18-hydrogen backflow support plate

Detailed Description

In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.

As shown in fig. 1 and 2, the main body of the hydrogen fuel combustion chamber head structure of the runway type jet hole provided by the application is an annular deflector disk 10, and a larger central channel 17 is arranged at the center of the deflector disk 10 along the axial direction.

The left end face of the guide disc 10 is an air inlet end face 11, and the right end face of the guide disc 10 is an air outlet end face 12. At least one annular mixing groove 16 is provided on the air outlet end face 12 of the deflector disk 10. In the preferred embodiment illustrated in the present application, the number of the annular blending grooves 16 is two or more, and by providing two or more blending grooves 16, it is possible to form a secondary swirling flow between two adjacent blending grooves 16 in addition to a swirling flow in the blending grooves 16, thereby improving the blending capability.

On the radially inner and outer sides of the mixing groove 16 of the diaphragm 10, n+1 hydrogen deflectors 18 are formed, N being the number of mixing grooves 16. For example, in the embodiment shown in FIG. 1, there are two mixing tanks 16 and three hydrogen baffles 18.

Along the hydrogen guide plate 18 (or the axial direction of the guide disk 10), a non-passing annular hydrogen injection channel 14 is arranged from the air inlet end surface 11 to the air outlet end surface 12 of the guide disk 10. At the end of the hydrogen injection passage 14 (the side close to the exhaust end face 12), a plurality of hydrogen jet holes 15 distributed circumferentially in the radial direction are provided from both side wall faces of the blending groove 16, and the hydrogen jet holes 15 communicate the blending groove 16 and the hydrogen injection passage 14.

In the preferred embodiment of the present application, the number of the hydrogen jet holes 15 provided on the inner wall surface and the outer wall surface of the blending groove 16 is the same. In the embodiment shown in fig. 2, the two mixing tanks 16 have four walls, and the four walls have the same number of the

hydrogen jet holes

15, and 16 walls are provided on the same radius.

A plurality of runway type air jet holes 13 are arranged on the guide disc 10 at positions matched with the hydrogen jet holes 15, and the air jet holes 13 penetrate through two sides of the guide disc 10 to be communicated with the air inlet end face 11 and the mixing groove 16. The runway is composed of two semicircles and a rectangle between the semicircles. Wherein the width of the air jet hole 13 (i.e., the diameter of the semicircle) is much larger than the diameter of the hydrogen jet hole 15, and the air jet hole 13 is spaced apart from the sidewall of the mixing groove 16. Preferably, the center of the air jet hole 13 is located on a circular ring of the radial width center line of the mixing groove 16, and the length direction of the air jet hole 13 is directed to the center of the diaphragm 10. The spacing between the air jet holes 13 distributed over the radial width centerline circles of different diameters is different, such as in the embodiment shown in FIG. 2, the spacing of the air jet holes 13 on the radial width centerline circle of the outer blending groove 16 is greater than the spacing of the air jet holes 13 on the radial width centerline circle of the inner blending groove 16.

In some embodiments of the present application, the hydrogen fuel combustion chamber head structure may be manufactured as an integrated structure by an additive manufacturing method, so as to solve the problems of more hydrogen jet holes 15 and complicated hydrogen or air flow paths.

In use, the main stream air Q1 flows into the air jet holes 13 from the air inlet end face 11 side of the baffle plate 10 along the horizontal direction or the axial direction, the hydrogen Q2 flows into the hydrogen injection channel 14 from the air inlet end face 11 side of the baffle plate 10 along the horizontal direction or the axial direction, the hydrogen is vertically jetted into the mixing groove 16 through the circumferentially distributed hydrogen jet holes 15, and is fully mixed with the main stream air Q1 flowing in the air jet holes 13, and a pair of backflow areas (called inner backflow areas) are generated at the outlet of each pair of air jet holes 15 in the mixing groove 16 for holding micro flame clusters and stabilizing flames. At the same time, a pair of recirculation zones, called outer recirculation zones, are also formed on the surface of the hydrogen baffle 18 between two adjacent blending tanks 16, which further stabilize the flame. Through the multi-point jet layout form, the air and the hydrogen are fully mixed, the combustion efficiency is high, the flame size is short, and the NOx emission is greatly reduced. In addition, because the hydrogen combustion rate is high, the length of the flame tube is shorter, and the saved cooling gas can be used for lean oil mixed combustion at the head part of the combustion chamber, so that the NOx emission is further reduced.

The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A hydrogen fuel combustion chamber head structure of a racetrack jet hole, comprising:

the air guide device comprises a guide disc (10), wherein one side of the guide disc (10) is an air inlet end face (11), the other side of the guide disc is an air outlet end face (12), and at least one annular mixing groove (16) is formed in the air outlet end face (12) of the guide disc (10);

the two radial sides of the mixing groove (16) are provided with hydrogen guide plates (18);

a non-penetrating hydrogen injection channel (14) extending along the axis is arranged on the hydrogen guide plate (18) from the air inlet end face (11) to the air outlet end face (12), a plurality of circumferentially distributed and radially extending hydrogen jet holes (15) are arranged at the tail end of the hydrogen injection channel (14) close to the air outlet end face (12), and the hydrogen jet holes (15) are communicated with the mixing groove (16) and the hydrogen injection channel (14);

the air jet holes (13) are arranged on the guide disc (10) at positions matched with the hydrogen jet holes (15), the air jet holes (13) penetrate through two sides of the guide disc (10) and are communicated with the air inlet end face (11) and the mixing groove (16), the air jet holes (13) are in a runway shape, and the runway shape is formed by two semicircles and a rectangle between the semicircles.

2. The hydrogen fuel combustion chamber head structure of a racetrack jet hole of claim 1, wherein the blending slots (16) are two or more.

3. The hydrogen fuel combustion chamber head structure of a racetrack jet hole as claimed in claim 1, wherein the number of the hydrogen deflectors (18) is (n+1), and N is the number of the mixing grooves (16).

4. The hydrogen fuel combustion chamber head structure of a racetrack type jet hole as claimed in claim 2, wherein the number of the hydrogen jet holes (15) provided on the side wall surface of the blending groove (16) is the same.

5. The hydrogen fuel combustion chamber head structure of a racetrack type jet hole as claimed in claim 4, wherein a width of the air jet hole (13) is larger than a diameter of the hydrogen jet hole (15), and the air jet hole (13) is spaced apart from a side wall of the mixing groove (16).

6. The hydrogen fuel combustion chamber head structure of a racetrack type jet hole as claimed in claim 5, wherein a center of the air jet hole (13) is located on a circular ring of a radial width center line of the mixing tank, and a length direction of the air jet hole (13) is directed to a center of the diaphragm (10).

7. The hydrogen fuel combustion chamber head structure of a racetrack type jet hole as claimed in claim 6, wherein the air jet holes (13) distributed on the radial width centerline rings of different blend groove (16) diameters are different in pitch.

8. A hydrogen fuel combustion chamber head structure of a racetrack jet hole as claimed in any one of claims 1 to 7, wherein the hydrogen fuel combustion chamber head structure is fabricated as a unitary structure by additive manufacturing.