External secondary air passage air extraction structure for aeroengine combustor test

Abstract

The present invention discloses an air extraction structure for the outer secondary air passage in the combustion chamber test of an aeroengine, which can simulate the actual working conditions by discharging the air flow in the outer secondary air passage to the downstream end. Since the air extraction structure can achieve the discharge of the air flow in the outer secondary air passage to the downstream end to simulate the actual working conditions, it solves the problem in the prior art that the air flow in the outer secondary air passage flows out in the middle, which affects the flow field of the outer secondary air passage, and ensures the stability of the flow field of the outer secondary air passage.

Description

Technical Field

[0001] The present invention relates to an external secondary air passage air extraction structure for an aero-engine combustion chamber test, belonging to the technical field of aero-engine tests. Background Art

[0002] The combustion chamber is an essential and important component of an aero-gas turbine engine. During the test of the combustion chamber component, the flame tube mounting flange 8 at the combustion chamber outlet is directly connected to the flange 10 of the measurement section. A temperature measuring sensor 16 is installed on the measurement section to measure the outlet temperature during the performance test of the combustion chamber. However, after installing the temperature measuring sensor 16 on the measurement section, the flange 10 and the outer support ring 9 will block the external secondary air passage 5 of the combustion chamber. The prior art is to set external secondary air passage air holes 21 on the casing 3, and install an air extraction pipeline 22 outside the casing 3 at the position of the external secondary air passage air holes 21 to communicate with the external secondary air passage 5 for exhaust, as Figure 3 shown. Although the gas in the external secondary air passage 5 can be exhausted, since the air flow in the external secondary air passage 5 flows out in the middle and fails to simulate the actual working condition of flowing out from the downstream end of the installed temperature measuring sensor 16, there will be a problem of affecting the flow field of the external secondary air passage 5. The stability of the flow field of the external secondary air passage 5 is an important factor in ensuring efficient fuel combustion and preventing the flame tube 4 from being burned out. Summary of the Invention

[0003] To solve the above technical problems, the present invention provides an external secondary air passage air extraction structure for an aero-engine combustion chamber test.

[0004] The present invention is achieved through the following technical solutions.

[0005] An external secondary air passage air extraction structure for an aero-engine combustion chamber test provided by the present invention includes an air extraction structure that can simulate the actual working condition by discharging the air flow in the external secondary air passage to the downstream end.

[0006] The air extraction structure includes: a flange fixedly connected to the flame tube mounting flange at the combustion chamber outlet;

[0007] An outer support ring fixedly connected to the inner diameter space of the flange and the flame tube mounting flange. The outer support ring blocks the external secondary air passage of the combustion chamber, forming a flame tube mounting flange gap between the outer support ring and the flame tube mounting flange, and there is a rear end gap between the outer support ring and the flange;

[0008] A kidney-shaped hole provided on the outer support ring to communicate the flame tube mounting flange gap and the rear end gap;

[0009] An inner cylinder installed on the rear end of the outer support ring and the flange. A flange ring cavity with a trapezoidal structure on one side is formed between the inner cylinder and the flange. The inner cylinder at the flange ring cavity is provided with flange air film holes to communicate with the kidney-shaped hole.

[0010] The flange is fixedly connected to the installation edge of the combustion chamber outlet flame tube through bolts and nuts.

[0011] The outer support ring is fixedly connected to the installation edge of the flame tube through screws.

[0012] The inner cylinder is fixedly welded to the flange.

[0013] The air film holes of the flange are arranged obliquely from the outer support ring to the flange, and the obliquely arranged air film holes of the flange are combined with the flange ring cavity of the trapezoidal structure.

[0014] One more flow guiding block is fixedly added to the outer support ring and extends towards the inner wall surface of the inner cylinder, so that the air flow leaking between the outer support ring and the flange is discharged backward along the inner wall surface of the inner cylinder without affecting the parameter measurement of the temperature measuring sensor head.

[0015] The flow guiding block is integrally formed and fixed with the outer support ring.

[0016] The beneficial effect of the present invention is that: since the air extraction structure can realize the discharge of the air flow in the outer secondary air passage to the downstream end, which can simulate the actual working condition, it solves the problem that the air flow in the outer secondary air passage in the prior art flows out in the middle and affects the flow field of the outer secondary air passage, and ensures the stability of the flow field of the outer secondary air passage. Brief Description of the Drawings

[0017] Figure 1 is a schematic diagram of the air extraction structure of the present invention;

[0018] Figure 2 is Figure 1 a partial structural schematic diagram of;

[0019] Figure 3 is a schematic diagram of the prior art structure;

[0020] In the figure: 1 - diffuser; 2 - fuel nozzle; 3 - casing; 4 - flame tube; 5 - outer secondary air passage; 6 - clearance of the flame tube installation edge; 7 - kidney-shaped hole; 8 - flame tube installation edge; 9 - outer support ring; 10 - flange; 11 - flange ring cavity; 13 - inner cylinder; 14 - air film hole of the flange; 15 - flow guiding block; 16 - temperature measuring sensor head; 21 - air flow hole of the outer secondary air passage; 22 - air extraction pipeline. Detailed Embodiment

[0021] The technical solution of the present invention will be further described below, but the scope of protection claimed is not limited thereto.

[0022] As Figures 1 to 2 shown.

[0023] An external secondary air passage air extraction structure for an aeroengine combustion chamber test according to the present application. The combustion chamber is composed of components such as a diffuser 1, a fuel nozzle 2, a casing 3, a flame tube 4, and a flame tube mounting flange 8. An external secondary air passage 5 is formed between the casing 3 and the flame tube 4, which is prior art and will not be described further.

[0024] The air extraction structure includes a flange 10 that is tightly sealed and fixedly connected to the flame tube mounting flange 8 at the combustion chamber outlet through bolts and nuts.

[0025] An outer support ring 9 that is fixedly connected to the flame tube mounting flange 8 by screws in the inner diameter space of the flange 10. The outer support ring 9 blocks the external secondary air passage 5 of the combustion chamber, forming a flame tube mounting flange gap 6 between the outer support ring 9 and the flame tube mounting flange 8, and there is a rear end gap between the outer support ring 9 and the flange 10. A kidney-shaped hole 7 is provided on the outer support ring 9 to communicate the flame tube mounting flange gap 6 and the rear end gap.

[0026] Regarding the kidney-shaped hole 7, in the figure, one flame tube 4 is shown. An engine has x heads, and 2x kidney-shaped holes 7 are provided on the annular outer support ring 9. Two kidney-shaped holes 7 correspond to one head, and the radial position of the kidney-shaped hole 7 corresponds to the flame tube mounting flange gap 6. The effective flow area of the flange air film hole 14 is larger than the effective flow area of the 2x kidney-shaped holes 7 on the outer support ring 9, and throttling is achieved by using the kidney-shaped holes 7 of the outer support ring 9.

[0027] An inner cylinder 13 installed at the rear end of the outer support ring 9 and on the flange 10. The inner cylinder 13 is fixedly welded to the flange 10, and a flange ring cavity 11 with a trapezoidal structure on one side is formed between the inner cylinder 13 and the flange 10. The inner cylinder 13 located at the flange ring cavity 11 is provided with a flange air film hole 14 to communicate with the kidney-shaped hole 7.

[0028] When the temperature measurement sensor 16 is located inside the outer support ring 9 in the measurement section, the air flow in the external secondary air passage 5 can be discharged downstream through the flame tube mounting flange gap 6, the kidney-shaped hole 7, the rear end gap, and the flange air film hole 14. Since the air extraction structure can simulate the actual working condition by discharging the air flow in the external secondary air passage 5 downstream, it solves the problem in the prior art that the air flow in the external secondary air passage 5 flows out in the middle and affects the flow field of the external secondary air passage 5, and ensures the stability of the flow field of the external secondary air passage 5.

[0029] The flange air film hole 14 is inclined from the outer support ring 9 to the flange 10. The inclined flange air film hole 14 combined with the flange ring cavity 11 with a trapezoidal structure enables the cooling air to be discharged along the wall surface from the inner cylinder air film hole 14, forming an air film on the inner wall of the inner cylinder 13 to achieve cooling and protection of the inner cylinder 13.

[0030] To prevent gas leakage due to poor sealing between the outer support ring 9 and the flange 10, and the airflow blowing onto the temperature measurement sensor head 16 will affect data acquisition. Therefore, a flow guide block 15 is integrally formed and fixed on the outer support ring 9 and extends towards the inner wall surface of the inner cylinder 13, so that the leaked airflow between the outer support ring 9 and the flange 10 is discharged backward along the inner wall surface of the inner cylinder 13 without affecting the parameter measurement of the temperature measurement sensor head 16.

Claims

1. An external secondary air passage air extraction structure for an aero-engine combustion chamber test, characterized in that, Comprising: An air extraction structure that can simulate actual working conditions by discharging the air flow in the outer secondary air passage (5) to the downstream end; The air extraction structure includes: a flange (10) fixedly connected to the combustion chamber outlet flame tube mounting edge (8); An outer support ring (9) fixedly connected to the inner diameter space of the flange (10) and the flame tube mounting edge (8). The outer support ring (9) blocks the outer secondary air passage (5) of the combustion chamber, forming a flame tube mounting edge gap (6) between the outer support ring (9) and the flame tube mounting edge (8). There is a rear end gap between the outer support ring (9) and the flange (10); A kidney-shaped hole (7) provided on the outer support ring (9) to connect the flame tube mounting edge gap (6) and the rear end gap; An inner cylinder (13) mounted on the rear end of the outer support ring (9) and the flange (10). A flange ring cavity (11) with a trapezoidal structure on one side is formed between the inner cylinder (13) and the flange (10). The inner cylinder (13) located at the flange ring cavity (11) is provided with flange air film holes (14) to communicate with the kidney-shaped hole (7); The flange air film holes (14) are inclined from the outer support ring (9) to the flange (10), and the inclined flange air film holes (14) are combined with the trapezoidal flange ring cavity (11); A deflector block (15) is fixedly added to the outer support ring (9) and extends towards the inner wall surface of the inner cylinder (3).

2. The external secondary air passage air extraction structure for the aeroengine combustion chamber test according to claim 1, wherein: The flange (10) is fixedly connected to the combustion chamber outlet flame tube mounting edge (8) by bolts and nuts.

3. The outer secondary air passage air extraction structure for the aeroengine combustor test according to claim 1, characterized in that: The outer support ring (9) is fixedly connected to the flame tube mounting edge (8) by screws.

4. The outer secondary air passage air extraction structure for the aero-engine combustion chamber test according to claim 1, wherein: The inner cylinder (13) is fixedly welded to the flange (10).

5. The outer secondary air passage air extraction structure for the aeroengine combustor test according to claim 1, characterized in that: The deflector block (15) is integrally formed and fixed with the outer support ring (9).

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