Cooling design method for thrust augmentation flow guide supporting plate in afterburner of aero-engine

Abstract

The invention belongs to the technical field of design of thrust augmentation flow guide supporting plates in afterburners of aero-engines, and particularly relates to a cooling design method for the thrust augmentation flow guide supporting plates in the afterburners of the aero-engines, in particular to a cooling design method for the thrust augmentation flow guide supporting plates in the afterburners of the aero-engines. Based on the reality that the temperature distribution unevenness on the stress application flow guide supporting plate is large, the pressure distribution difference is large, and the outer culvert cooling air flow is limited, the area, needing to be cooled, on the stress application flow guide supporting plate is divided into a plurality of cooling elements for precise cooling design, the wall temperature gradient on the stress application flow guide supporting plate can be improved, the number of iterations can be reduced, and high efficiency is achieved.

Description

Technical Field

[0001] The present application belongs to the technical field of afterburner guide plate design in an afterburner combustion chamber of an aircraft engine, and specifically relates to a cooling design method for an afterburner guide plate in an afterburner combustion chamber of an aircraft engine. Background Art

[0002] The afterburner is an important component of the aircraft engine's rearward infrared radiation. Currently, most methods use an external air-cooled afterburner guide support plate to shield the hot end components to reduce the afterburner's rearward infrared radiation.

[0003] In the afterburner combustion chamber, due to the uneven inlet temperature field, there is a large degree of unevenness in the temperature distribution on the afterburner guide plate. The afterburner guide plate is located in the internal expansion flow path, the flow field distribution is complex, there are large differences in the pressure distribution on the afterburner guide plate, and the external culvert cooling air flow is limited. It is necessary to increase the cooling efficiency of the external culvert cooling air as much as possible and carry out precise cooling design for the afterburner guide plate.

[0004] At present, the cooling design of afterburner guide plate is mostly carried out based on the method of thermo-solid coupling 3D simulation. First, the wall temperature distribution of the afterburner guide plate is obtained through thermo-solid coupling 3D simulation. Then, according to the wall temperature distribution and the cooling holes roughly arranged according to experience, the wall temperature, flow rate and pressure ratio are checked and adjusted again through thermo-solid coupling 3D simulation. This method is difficult to adapt to the precise design of afterburner guide plate cooling when the temperature distribution on the afterburner guide plate is relatively uneven, the pressure distribution is relatively different and the external cooling air flow is limited. It requires multiple rounds of iterations, which is time-consuming and laborious.

[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0006] The purpose of the present application is to provide a cooling design method for an afterburner guide plate in an afterburner combustion chamber of an aircraft engine, so as to overcome or alleviate at least one of the known technical defects.

[0007] The technical solution of this application is: A cooling design method for an afterburner guide plate in an afterburner combustion chamber of an aircraft engine, comprising: Step 1: Determine the area on the booster guide plate that needs cooling; Step 2: Divide the area to be cooled into multiple cooling elements; Step 3: Use the three-dimensional simulation of thermal-solid coupling to calculate the heat transfer characteristic parameters of each cooling unit under typical working conditions, including the actual flow rate of each single hole in each cooling unit when the cooling hole is open. , the blowing ratio of cooling air jet to mainstream , the static pressure at the corresponding position of the cooling hole in each cooling element when the cooling hole is not opened , wall temperature ; Step 4: Preliminarily determine the total amount of cooling air for the afterburner guide plate , based on the static pressure at the corresponding position of the cooling hole in each cooling element without opening the cooling hole , wall temperature , calculate the amount of cooling gas required for each cooling unit ; Step 5: Calculate the amount of cooling gas required for each cooling unit , and the actual flow rate of a single hole in the cooling unit , calculate the cooling hole area , and then calculate the total number of cooling holes , Opening rate ; Step 6: Total number of cooling holes based on each cooling element , Opening rate , determine the axial spacing of cooling holes and radial spacing ; Step 7: According to the axial spacing of cooling holes of each cooling element and radial spacing , Opening rate , Aperture , and the blowing ratio of the cooling air jet to the mainstream , the comprehensive film cooling efficiency is calculated ; Step 8: Based on the comprehensive film cooling efficiency of each cooling unit , and the hot gas side temperature of the afterburner guide plate , Air conditioning side temperature , calculate the wall temperature of each cooling element ; Step 9: Determine the wall temperature of each cooling unit , whether the average wall temperature of the afterburner guide plate is met , maximum wall temperature If not, adjust the cooling air volume of the booster guide plate , return to step 4.

[0008] Optionally, in the above-mentioned afterburner guide plate cooling design method in the afterburner combustion chamber of an aircraft engine, step five includes: ; in, is the area of ​​the cooling element.

[0009] Optionally, in the above-mentioned afterburner guide plate cooling design method in the afterburner combustion chamber of an aircraft engine, step eight includes: .

[0010] Optionally, the above-mentioned afterburner guide plate cooling design method in the afterburner combustion chamber of an aircraft engine further includes: Step 10: Use the thermo-solid coupling 3D simulation to check the afterburner guide plate. If the check fails, the total amount of cooling air for the afterburner guide plate is , return to step 4.

[0011] Optionally, in the above-mentioned afterburner guide plate cooling design method in the afterburner combustion chamber of the aircraft engine, in step 10, the content of the afterburner guide plate verification includes the actual amount of cooling air for the afterburner guide plate. , average wall temperature , maximum wall temperature And the external pressure ratio .

[0012] According to at least one embodiment of the present application, This application has at least the following beneficial technical effects: A cooling design method for afterburner guide plates in afterburner combustion chambers of aircraft engines is provided. Based on the fact that the temperature distribution on the afterburner guide plates is relatively uneven, the pressure distribution is relatively different, and the external cooling airflow is limited, the area to be cooled on the afterburner guide plates is divided into multiple cooling primitives for precise cooling design, which can improve the temperature gradient on the wall of the afterburner guide plates, reduce the number of iterations, and has high efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of a cooling design method for afterburner guide struts in an afterburner combustion chamber of an aircraft engine provided in an embodiment of the present application.

[0014] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0015] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0016] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0017] A cooling design method for afterburner guide plate in afterburner combustion chamber of an aircraft engine, such as Figure 1 shown.

[0018] The inputs for cooling design of afterburner guide plate mainly include the profile structure of afterburner guide plate, average wall temperature , maximum wall temperature As well as hot air side aerodynamic parameters, cold air side aerodynamic parameters, etc., among which the hot air side aerodynamic parameters are the inherent aerodynamic parameters, including temperature ,pressure ,speed etc.; aerodynamic parameters on the cold air side, i.e., external aerodynamic parameters, including temperature ,pressure ,speed wait.

[0019] Step 1: Determine the area on the afterburner guide plate that needs cooling.

[0020] Calculate the area of ​​the cooling area of ​​the booster guide plate .

[0021] Step 2: Divide the area to be cooled into multiple cooling elements.

[0022] The area to be cooled can be divided into cooling units, and the area of ​​each cooling unit is recorded as .

[0023] Step 3: Use thermal-solid coupling 3D simulation to calculate the heat transfer characteristic parameters of each cooling unit under typical working conditions, including the actual flow rate of each single hole in each cooling unit when the cooling hole is open. , Flow coefficient , the blowing ratio of cooling air jet to mainstream The single hole area is , the static pressure at the corresponding position of the cooling hole in each cooling element when the cooling hole is not opened , wall temperature .

[0024] Step 4: Preliminarily determine the total amount of cooling air for the afterburner guide plate , based on the static pressure at the corresponding position of the cooling hole in each cooling element without opening the cooling hole , wall temperature , calculate the amount of cooling gas required for each cooling unit .

[0025] Step 5: Calculate the amount of cooling gas required for each cooling unit , and the actual flow rate of a single hole in the cooling unit , calculate the cooling hole area , and then calculate the total number of cooling holes , Opening rate .

[0026] .

[0027] Step 6: Total number of cooling holes based on each cooling element , Opening rate , determine the axial spacing of cooling holes and radial spacing .

[0028] The axial spacing of the cooling holes of each cooling element can be determined based on the basic heat transfer characteristics of the afterburner guide plate. and radial spacing .

[0029] Step 7: According to the axial spacing of cooling holes of each cooling element and radial spacing , Opening rate , Aperture , and the blowing ratio of the cooling air jet to the mainstream , the comprehensive film cooling efficiency is calculated .

[0030] Step 8: Based on the comprehensive film cooling efficiency of each cooling unit , and the hot gas side temperature of the afterburner guide plate , Air conditioning side temperature , calculate the wall temperature of each cooling element .

[0031] .

[0032] Step 9: Determine the wall temperature of each cooling unit , whether the average wall temperature of the afterburner guide plate is met , maximum wall temperature If not, adjust the cooling air volume of the booster guide plate , return to step 4.

[0033] Step 10: Use the thermo-solid coupling 3D simulation to check the afterburner guide plate. If the check fails, the total amount of cooling air for the afterburner guide plate is , return to step 4.

[0034] The contents of the afterburner guide plate verification include the actual amount of cooling air used by the afterburner guide plate , average wall temperature , maximum wall temperature And the external-to-internal pressure ratio wait.

[0035] The cooling design method for the afterburner guide plate in the afterburner combustion chamber of an aircraft engine disclosed in the above-mentioned embodiment is based on the fact that the temperature distribution on the afterburner guide plate is relatively uneven, the pressure distribution difference is relatively large, and the external cooling air flow is limited. The area to be cooled on the afterburner guide plate is divided into multiple cooling elements for precise cooling design. This can improve the temperature gradient on the wall of the afterburner guide plate, reduce the number of iterations, and has high efficiency.

[0036] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A cooling design method for afterburner guide plate in afterburner combustion chamber of an aircraft engine, characterized in that: include: Step 1: Determine the area on the booster guide plate that needs cooling; Step 2: Divide the area to be cooled into multiple cooling elements; Step 3: Use the three-dimensional simulation of thermal-solid coupling to calculate the heat transfer characteristic parameters of each cooling unit under typical working conditions, including the actual flow rate of each single hole in each cooling unit when the cooling hole is open. , the blowing ratio of cooling air jet to mainstream , the static pressure at the corresponding position of the cooling hole in each cooling element when the cooling hole is not opened , wall temperature ; Step 4: Preliminarily determine the total amount of cooling air for the afterburner guide plate , based on the static pressure at the corresponding position of the cooling hole in each cooling element without opening the cooling hole , wall temperature , calculate the amount of cooling gas required for each cooling unit ; Step 5: Calculate the amount of cooling gas required for each cooling unit , and the actual flow rate of a single hole in the cooling unit , calculate the cooling hole area , and then calculate the total number of cooling holes , Opening rate ; Step 6: Total number of cooling holes based on each cooling element , Opening rate , determine the axial spacing of cooling holes and radial spacing ; Step 7: According to the axial spacing of cooling holes of each cooling element and radial spacing , Opening rate , Aperture , and the blowing ratio of the cooling air jet to the mainstream , the comprehensive film cooling efficiency is calculated ; Step 8: Based on the comprehensive film cooling efficiency of each cooling unit , and the hot gas side temperature of the afterburner guide plate , Air conditioning side temperature , calculate the wall temperature of each cooling element ; Step 9: Determine the wall temperature of each cooling unit , whether the average wall temperature of the afterburner guide plate is met , maximum wall temperature If not, adjust the cooling air volume of the booster guide plate , return to step 4.

2. The cooling design method for afterburner guide plate in afterburner combustion chamber of an aircraft engine according to claim 1, characterized in that: In step five, there are: ； in, is the area of ​​the cooling element.

3. The cooling design method for afterburner guide plate in afterburner combustion chamber of an aircraft engine according to claim 1, characterized in that: In step eight: 。 4. The cooling design method for afterburner guide plate in afterburner combustion chamber of an aircraft engine according to claim 1, characterized in that: Also includes: Step 10: Use the thermo-solid coupling 3D simulation to check the afterburner guide plate. If the check fails, the total amount of cooling air for the afterburner guide plate is , return to step 4.

5. The cooling design method for afterburner guide plate in afterburner combustion chamber of an aircraft engine according to claim 4, characterized in that: In step 10, the contents of the verification of the afterburner guide plate include the actual amount of cooling air used by the afterburner guide plate , average wall temperature , maximum wall temperature And the external-to-internal pressure ratio .

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