A detachable staged combustion cyclone

Abstract

The present invention discloses a detachable staged combustion swirler, which belongs to the field of design and application of aircraft engine combustion chamber test pieces. The pre-combustion stage swirler includes a pre-combustion stage swirler inner ring wall, a pre-combustion stage swirler outer ring wall and a plurality of pre-combustion stage axial blades fixedly connected therebetween, the outer ring wall of the swirler is installed with an interference fit to the inner wall of the main pre-combustion stage connecting section; a plurality of main combustion stage positioning bosses are also fixedly connected to the outer wall of the main pre-combustion stage connecting section; the main combustion stage swirler includes a main combustion stage axial blade, a main combustion stage outlet roar and a main combustion stage swirler inner ring wall, and a plurality of main combustion stage positioning grooves for accommodating the main combustion stage positioning bosses are fixedly connected to the inner wall of the main combustion stage swirler inner ring wall. The present invention ensures the integrity of the performance and structure of the swirler, and can also greatly shorten the processing cycle and economic cost, and has great practical significance.

Description

Technical Field

[0001] The invention relates to a design method for a detachable staged combustion swirler, and belongs to the field of design and application of aircraft engine combustion chamber test pieces. Background Art

[0002] The new generation of military aircraft pursues high maneuverability, supersonic cruise, short take-off, vertical landing and other performances, and the requirements for engine thrust-to-weight ratio are constantly increasing. The direct and effective way to improve the engine thrust-to-weight ratio is to increase the engine oil-to-gas ratio. Therefore, it is necessary to continuously improve and propose new high oil-to-gas ratio combustion organization methods to meet the increasingly high power requirements of the engine. The technical challenges faced by high oil-to-gas ratio combustion chambers mainly include expanding the stable working range of the combustion chamber, solving the problems of lean oil flameout under small working conditions and exhaust smoke under large working conditions. The staged combustion swirl organization came into being under this background. The staged combustion chamber has the characteristics of high combustion air volume and controllable fuel staging, which can effectively overcome the above technical challenges. The performance of the staged combustion chamber mainly depends on the structure of the staged swirler. Therefore, it is necessary to study the influence of the swirler structural parameters on the performance of the staged combustion chamber.

[0003] There are many factors that affect the swirler structure. When exploring the influence of the swirler structure on the performance of the staged combustion chamber, it is often necessary to design multiple sets of swirler test pieces with different structures. The main configurations of swirlers with different structures are similar, and the swirlers are difficult to process and expensive to manufacture. Therefore, for staged combustion swirlers with different structures, the traditional integrated swirler design and processing method has no advantages in terms of processing time cycle and cost, and the independent processing of swirlers with different structures may cause greater errors, which is not conducive to the study of the law of the influence of swirler structure on the performance of the staged combustion chamber. Summary of the invention

[0004] In view of the above problems, the present invention proposes a detachable staged combustion cyclone, which solves the problem of streamlined design and processing of the staged combustion cyclone. The staged combustion cyclone is divided into three components: a pre-combustion stage cyclone, a main pre-combustion stage connecting section, and a main combustion stage cyclone. The performance and structural integrity of the cyclone are ensured through clever overlap and interference fit, and different components can be disassembled to achieve staged combustion cyclone tests with different structures.

[0005] The technical solution of the present invention is: the staged combustion swirler comprises a pre-combustion stage swirler 1, a main pre-combustion stage connecting section 2 and a main combustion stage swirler 3 which are detachably connected in sequence from the inside to the outside; so that each component can be used as an independent factor to study the influence of the swirler structure on the performance of the staged combustion chamber.

[0006] The pre-combustion stage swirler 1 comprises a pre-combustion stage swirler inner annular wall 1b, a pre-combustion stage swirler outer annular wall 1c and a plurality of pre-combustion stage axial blades 1a fixedly connected therebetween, one side end face of the pre-combustion stage swirler outer annular wall 1c is a pre-combustion stage swirler outlet platform 1d; the swirler outer annular wall 1c is installed with an interference fit with the inner wall of the main pre-combustion stage connecting section 2, and is positioned by the swirler outlet platform 1d, and a positioning platform 2a for abutting against the swirler outlet platform 1d is provided on the inner wall of the main pre-combustion stage connecting section 2;

[0007] A plurality of main combustion stage positioning bosses 2b are also fixedly connected to the outer wall of the main pre-combustion stage connecting section 2;

[0008] The main combustion stage swirler 3 includes main combustion stage axial blades 3a, a main combustion stage outlet roar 3c and a main combustion stage swirler inner ring wall 3e. The main combustion stage swirler inner ring wall 3e is coaxially arranged in the main combustion stage outlet roar 3c, and the two are fixedly connected by a plurality of main combustion stage axial blades 3a; a plurality of main combustion stage positioning grooves 3b for accommodating the main combustion stage positioning boss 2b are fixedly connected on the inner wall of the main combustion stage swirler inner ring wall 3e, so that the gap between the main combustion stage swirler inner ring wall 3e and the main pre-combustion stage connecting section 2 is changed to the main combustion stage non-swirling channel as described now; a main combustion stage swirler mounting seat 3d for connecting the combustion chamber head baffle is also fixedly connected on the outer wall of the main combustion stage outlet roar 3c.

[0009] Preferably, after assembly, the positioning platform 2a fits the cyclone outlet platform 1d.

[0010] Preferably, the main combustion stage annular oil chamber 2c, the connecting section annular seam 2e and the main combustion stage direct-injection nozzle 2d which are connected in sequence are provided in the main pre-combustion stage connecting section 2, and an outlet sleeve 2f located at the outlet side of the pre-combustion stage swirler 1 is also fixedly connected to the inner wall of the main pre-combustion stage connecting section 2. Thus, the structure and position of the main combustion stage nozzle 2d and the pre-combustion stage nozzle are fixed, and the uniformity of the spray characteristics of the swirlers with different structures is ensured.

[0011] Preferably, the main combustion stage swirler inner annular wall 3e overlaps with the main pre-combustion stage connecting section 2 to form a main combustion stage non-swirling channel.

[0012] The main combustion stage positioning groove 3b is provided with a T-shaped groove or an L-shaped groove.

[0013] Preferably, the outer diameter of the pre-combustion stage axial blade 1a is smaller than the inner diameter of the main combustion stage annular oil cavity 2c, and the inner diameter of the pre-combustion stage axial blade 1a is larger than the inner diameter of the swirler inner annular wall 1b, so that a variety of pre-combustion stage swirler blade schemes that meet design requirements can be realized.

[0014] Preferably, the outer diameter of the main combustion stage blade 3a is smaller than the outer diameter of the main combustion stage mounting seat 3d, and the inner diameter of the main combustion stage blade 3a is not smaller than the inner diameter of the main combustion stage positioning groove 3b.

[0015] The above-mentioned size design can achieve the purpose of disassembling and reassembling the components, thereby achieving flexible replacement of the components and individual exploration of the effects of each component.

[0016] The present invention divides the staged combustion cyclone into three components: a pre-combustion stage, a main pre-combustion stage connecting section and a main combustion stage. Each component can be used as an independent influencing factor to study the influence of the cyclone structure on the performance of the staged combustion chamber. The present invention ensures the integrity of the cyclone performance and structure, and can also greatly shorten the processing cycle and economic cost, which has great practical significance.

[0017] The advantages of the present invention compared with the prior art are as follows:

[0018] 1. Under the condition of meeting the test technical requirements, the main structures of the cyclone can be disassembled and processed separately, avoiding the integrated processing of cyclones with multiple structure graded combustion;

[0019] Second, the differences in the airflow channel structure caused by processing various staged combustion cyclone test pieces are reduced, and the test accuracy is improved;

[0020] 3. Greatly shortened the processing cycle and economic cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic diagram of a staged combustion cyclone.

[0022] Figure 2-1 is a schematic diagram of a staged combustion cyclone.

[0023] Figure 2-2 yes Figure 2-1 AA section view,

[0024] Figure 3 is a schematic diagram of the pre-combustion stage cyclone.

[0025] Figure 4-1 This is a schematic diagram of the main pre-combustion stage connection section.

[0026] Figure 4-2 is an axial cross-section of the main pre-combustion stage connection section.

[0027] Figure 5-1 This is a schematic diagram of the main combustion stage.

[0028] Figure 5-2 is an axial section of the main combustion stage;

[0029] In the figure: 1 is a pre-combustion stage swirler, 1a is a pre-combustion stage axial blade, 1b is an inner annular wall of the pre-combustion stage swirler, 1c is an outer annular wall of the pre-combustion stage swirler, and 1d is an outlet platform of the swirler;

[0030] 2 is the main pre-combustion stage connection section, 2a is the pre-combustion stage positioning platform, 2b is the main combustion stage positioning boss, 2c is the main combustion stage annular oil cavity, 2d is the main combustion stage direct injection nozzle, 2e is the connection section annular seam, 2f is the outlet sleeve, and 2g is the contraction section in the main combustion stage outlet channel;

[0031] 3 is the main combustion stage swirler, 3a is the main combustion stage axial blade, 3b is the main combustion stage positioning groove, 3c is the main combustion stage outlet roar, 3d is the main combustion stage swirler mounting seat, and 3e is the main combustion stage swirler inner ring wall. Implementation

[0032] In order to clearly illustrate the technical features of this patent, this patent is elaborated in detail below through a specific implementation method and in combination with its accompanying drawings.

[0033] The specific implementation process of this case is as follows: Figure 1 , 2-1 As shown in 2-2, the graded cyclone is divided into a pre-combustion stage cyclone 1, a main pre-combustion stage connecting section 2, a main combustion stage cyclone 3 and other components. Each component can be replaced separately to realize graded cyclone test pieces with different structures.

[0034] Among them Figure 3 As shown, the pre-combustion stage swirler 1 includes pre-combustion stage axial blades 1a, pre-combustion stage swirler inner annular wall 1b, pre-combustion stage swirler outer annular wall 1c, and swirler outlet platform 1d. The upper end surface of the pre-combustion stage swirler inner annular wall 1b can be used to position and install the pre-combustion stage centrifugal nozzle.

[0035] like Figure 4-1 , 4-2 As shown, the main pre-combustion stage connecting section 2 includes a pre-combustion stage positioning platform 2a, a main combustion stage positioning boss 2b, a main combustion stage annular oil chamber 2c, a main combustion stage direct-injection nozzle 2d, a connecting section annular seam 2e, an outlet sleeve 2f, a contraction section 2g in the main combustion stage outlet channel, etc. It is positioned and matched with the outer annular wall 1c of the pre-combustion stage swirler through the positioning platform 2a, and is positioned and matched with the main combustion stage swirler 3 through the positioning boss 2b.

[0036] like Figure 5-1 , 5-2 As shown, the main combustion stage swirler 3 includes main combustion stage axial blades 3a, main combustion stage positioning grooves 3b, main combustion stage outlet roar 3c, main combustion stage swirler mounting seat 3d, main combustion stage swirler inner ring wall 3e and other parts. The main combustion stage swirler mounting seat 3d is used to install and fix the main combustion stage swirler on the combustion chamber head baffle.

[0037] There are many specific implementation ways of the present invention. The above is only the preferred implementation mode of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements can be made without departing from the principle of the present invention. These improvements should also be regarded as the protection scope of the present invention.

Claims

1. A removable staged combustion cyclone, characterized in that: The staged combustion cyclone comprises, from the inside to the outside, a pre-combustion stage cyclone (1), a main pre-combustion stage connecting section (2), and a main combustion stage cyclone (3) which are detachably connected in sequence; The pre-combustion stage swirler (1) comprises a pre-combustion stage swirler inner ring wall (1b), a pre-combustion stage swirler outer ring wall (1c), and a plurality of pre-combustion stage axial blades (1a) fixedly connected therebetween, one side end surface of the pre-combustion stage swirler outer ring wall (1c) being a pre-combustion stage swirler outlet platform (1d); the swirler outer ring wall (1c) is installed with an interference fit with the inner wall of the main pre-combustion stage connecting section (2), and is positioned by the swirler outlet platform (1d); a positioning platform (2a) for abutting against the swirler outlet platform (1d) is provided on the inner wall of the main pre-combustion stage connecting section (2); A plurality of main combustion stage positioning bosses (2b) are also fixedly connected to the outer wall of the main pre-combustion stage connecting section (2); The main combustion stage swirler (3) comprises main combustion stage axial blades (3a), a main combustion stage outlet roar duct (3c) and a main combustion stage swirler inner ring wall (3e), wherein the main combustion stage swirler inner ring wall (3e) is coaxially arranged in the main combustion stage outlet roar duct (3c), and the two are fixedly connected via a plurality of main combustion stage axial blades (3a); a plurality of main combustion stage positioning grooves (3b) for accommodating the main combustion stage positioning bosses (2b) are fixedly connected to the inner wall of the main combustion stage swirler inner ring wall (3e), so that the gap between the main combustion stage swirler inner ring wall (3e) and the main pre-combustion stage connecting section (2) is the main combustion stage non-swirling channel; a main combustion stage swirler mounting seat (3d) for connecting to the combustion chamber head baffle is also fixedly connected to the outer wall of the main combustion stage outlet roar duct (3c); The main combustion stage swirler inner ring wall (3e) is overlapped with the main pre-combustion stage connecting section (2) to form a main combustion stage non-swirling channel; and a T-shaped groove or an L-shaped groove is provided in the main combustion stage positioning groove (3b).

2. A detachable staged combustion cyclone according to claim 1, characterized in that: After assembly, the positioning platform (2a) fits the cyclone outlet platform (1d).

3. The detachable staged combustion cyclone according to claim 1, characterized in that: The main pre-combustion stage connecting section (2) is provided with a main combustion stage annular oil chamber (2c), a connecting section annular seam (2e), and a main combustion stage direct-injection nozzle (2d) which are connected in sequence. An outlet sleeve (2f) located at the outlet side of the pre-combustion stage swirler (1) is also fixedly connected to the inner wall of the main pre-combustion stage connecting section (2).

4. The detachable staged combustion cyclone according to claim 1, characterized in that: The outer diameter of the pre-combustion stage axial blade (1a) is smaller than the inner diameter of the main combustion stage annular oil chamber (2c), and the inner diameter of the pre-combustion stage axial blade (1a) is larger than the inner diameter of the cyclone inner annular wall (1b).

5. The detachable staged combustion cyclone according to claim 1, characterized in that: The outer diameter of the main combustion stage blade (3a) is smaller than the outer diameter of the main combustion stage mounting seat (3d), and the inner diameter of the main combustion stage blade (3a) is not smaller than the inner diameter of the main combustion stage positioning groove (3b).

Images