A method for cooling design of a thrust guide vane in a turbofan engine afterburner

Abstract

The application belongs to the technical field of the design of a thrust guide vane in a turbofan engine afterburner, and particularly relates to a cooling design method for the thrust guide vane in the turbofan engine afterburner, and particularly relates to a cooling design method for the thrust guide vane in the turbofan engine afterburner, based on the actuality that the temperature distribution on the thrust guide vane is highly uneven, the pressure distribution is highly different, and the outer-casing cooling gas flow is limited, the cooling region on the thrust guide vane is divided into multiple cooling cells for precise cooling design, the wall temperature gradient on the thrust guide vane can be improved, the iteration number is reduced, and the method has high efficiency.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of the design of a thrust guide vane in a turbojet engine afterburner, and particularly relates to a method for cooling design of a thrust guide vane in a turbojet engine afterburner. BACKGROUND

[0002] The afterburner is an important component of the backward infrared radiation of the turbojet engine. At present, the method of shielding the hot end component by using the outer-duct air-cooled thrust guide vane is adopted to reduce the backward infrared radiation of the afterburner.

[0003] In the afterburner, due to the non-uniformity of the inlet temperature field, the temperature distribution on the thrust guide vane is greatly uneven. Moreover, the thrust guide vane is located in the inner-duct diffuser flow path, and the flow field distribution is complex. The pressure distribution on the thrust guide vane has a large difference. Moreover, the outer-duct cooling air flow is limited. Therefore, it is necessary to improve the cooling efficiency of the outer-duct cooling air as much as possible and accurately design the cooling of the thrust guide vane.

[0004] At present, the cooling design of the thrust guide vane is mostly based on the method of thermal-structural coupling three-dimensional simulation. First, the wall temperature distribution of the thrust guide vane is obtained through thermal-structural coupling three-dimensional simulation. Then, the cooling holes are roughly arranged according to the wall temperature distribution and experience. Finally, the wall temperature, flow rate, and pressure ratio are checked and adjusted through thermal-structural coupling three-dimensional simulation again. This method cannot adapt to the accurate design of the cooling of the thrust guide vane under the condition of great unevenness of the temperature distribution, great difference of the pressure distribution, and limited outer-duct cooling air flow. Therefore, it needs to be iterated for many rounds, which is time-consuming and laborious.

[0005] The present application is proposed in view of the above technical defects. SUMMARY

[0006] The purpose of the present application is to provide a method for cooling design of a thrust guide vane in a turbojet engine afterburner to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is as follows:

[0008] A method for cooling design of a thrust guide vane in a turbojet engine afterburner, comprising:

[0009] Step one, determining the cooling area on the thrust guide vane;

[0010] Step two, dividing the cooling area into a plurality of cooling elements;

[0011] Step three, calculating the heat transfer characteristic parameters of each cooling element under a typical working state point by thermal-structural coupling three-dimensional simulation, including the actual flow rate of each cooling element under the condition of opening the cooling hole The ratio of cooling air jet to mainstream airflow The static pressure at the corresponding position of the cooling hole in each cooling unit when the cooling holes are not open. , wall temperature ;

[0012] Step 4: Preliminary determination of the total cooling air volume for the booster guide plate Based on the static pressure at the corresponding positions of the cooling holes in each cooling unit without opening the cooling holes. , wall temperature Calculate the required cooling air volume for each cooling unit. ;

[0013] Step 5: Determine the required cooling air volume for each cooling unit. The actual flow rate of a single orifice within its cooling unit. The area of ​​the cooling holes was calculated. The total number of cooling holes can then be calculated. Opening ratio ;

[0014] Step 6: Based on the total number of cooling holes in each cooling element Opening ratio Determine the axial spacing of the cooling holes and radial spacing ;

[0015] Step 7: Based on the axial spacing of the cooling holes of each cooling element and radial spacing Opening ratio Aperture And the ratio of cooling air jet to mainstream airflow. The overall film cooling efficiency was calculated. ;

[0016] Step 8: Based on the overall film cooling efficiency of each cooling element And the temperature of the hot air side of the booster guide plate Cooling side temperature Calculate the wall temperature of each cooling unit. ;

[0017] Step 9: Determine the wall temperature of each cooling unit. Does it meet the average wall temperature requirement of the booster guide plate? , maximum wall temperature If not, adjust the total cooling air volume of the booster guide plate. Return to step four.

[0018] Optionally, in the above-mentioned design method for cooling the afterburner guide vanes in the afterburner chamber of an aero-engine, step five includes:

[0019] ;

[0020] wherein,

[0021] is the area of the cooling element.

[0022] Optionally, in the method for cooling design of the afterburner guide vane of the aero-engine, the step eight comprises the following steps:

[0023] .

[0024] Optionally, in the method for cooling design of the afterburner guide vane of the aero-engine, the method further comprises the following steps:

[0025] Step ten, checking the afterburner guide vane by using the thermal-solid coupling three-dimensional simulation, if the checking is not satisfied, returning to step four to adjust the total amount of cooling air of the afterburner guide vane.

[0026] Optionally, in the method for cooling design of the afterburner guide vane of the aero-engine, the content of checking the afterburner guide vane in step ten comprises the following steps: the actual amount of cooling air of the afterburner guide vane, the average wall temperature of the afterburner guide vane, the highest wall temperature of the afterburner guide vane, and the ratio of the outer and inner convection pressure.

[0027] According to at least one embodiment of the present application,

[0028] The present application has at least the following beneficial technical effects:

[0029] The present application provides a method for cooling design of the afterburner guide vane of the aero-engine, based on the actual situation that the temperature distribution of the afterburner guide vane is uneven, the pressure distribution is different, and the flow of the outer convection cooling air is limited, the cooling design of the afterburner guide vane is precisely designed by dividing the cooling area of the afterburner guide vane into multiple cooling elements, which can improve the wall temperature gradient of the afterburner guide vane and reduce the iteration number, and has high efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 is a schematic diagram of the method for cooling design of the afterburner guide vane of the aero-engine provided by the present application.

[0031] In order to better illustrate the present application, some contents of the drawings will be omitted, and only used for exemplary description, and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0032] ​In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described below in conjunction with the drawings. It should be understood that the specific embodiments described herein are only partial embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design.

[0033] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should be the general meanings understood by the general skilled person in the field of the present application. The words indicating the position used in the description of the present application are only used to indicate the relative direction or positional relationship, and the relative positional relationship may also change accordingly when the absolute position of the described object changes. The "comprising" used in the description of the present application indicates that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and other elements or objects are not excluded.

[0034] A cooling design method for a thrust guide vane in a turbofan engine afterburner, as shown in Figure 1 .

[0035] The inputs for the cooling design of the thrust guide vane mainly include the profile structure of the thrust guide vane, the average wall temperature , the maximum wall temperature , and the hot gas side aerodynamic parameters, the cold gas side aerodynamic parameters, etc., wherein the hot gas side aerodynamic parameters, i.e. the internal aerodynamic parameters, include temperature , pressure , velocity , etc.; the cold gas side aerodynamic parameters, i.e. the external aerodynamic parameters, include temperature , pressure , velocity , etc.

[0036] Step one, determine the cooling area on the thrust guide vane.

[0037] Calculate the area of the cooling area of the thrust guide vane .

[0038] Step two, divide the cooling area into multiple cooling elements.

[0039] The cooling area can be divided into cooling elements, and the area of each cooling element is denoted as .

[0040] Step three, perform thermal-solid coupling three-dimensional simulation to calculate the heat transfer characteristic parameters of each cooling element under a typical working state point, including the actual flow rate of each cooling element under the condition of opening cooling holes Flow coefficient The ratio of cooling air jet to mainstream airflow The area of ​​a single hole is The static pressure at the corresponding position of the cooling hole in each cooling unit when the cooling holes are not open. , wall temperature .

[0041] Step 4: Preliminary determination of the total cooling air volume for the booster guide plate Based on the static pressure at the corresponding positions of the cooling holes in each cooling unit without opening the cooling holes. , wall temperature Calculate the required cooling air volume for each cooling unit. .

[0042] Step 5: Determine the required cooling air volume for each cooling unit. The actual flow rate of a single orifice within its cooling unit. The area of ​​the cooling holes was calculated. The total number of cooling holes can then be calculated. Opening ratio .

[0043] .

[0044] Step 6: Based on the total number of cooling holes in each cooling element Opening ratio Determine the axial spacing of the cooling holes and radial spacing .

[0045] The axial spacing of the cooling holes in each cooling element can be determined based on the basic heat transfer characteristics of the booster plate. and radial spacing .

[0046] Step 7: Based on the axial spacing of the cooling holes of each cooling element and radial spacing Opening ratio Aperture And the ratio of cooling air jet to mainstream airflow. The overall film cooling efficiency was calculated. .

[0047] Step 8: Based on the overall film cooling efficiency of each cooling element And the temperature of the hot air side of the booster guide plate Cooling side temperature Calculate the wall temperature of each cooling unit. .

[0048] .

[0049] Step 9: Determine the wall temperature of each cooling unit. Does it meet the average wall temperature requirement of the booster guide plate? , maximum wall temperature If not, adjust the total cooling air volume of the booster guide plate. Return to step four.

[0050] Step 10: Verify the booster plate using a thermo-mechanical coupling 3D simulation. If the verification fails, adjust the total cooling air volume of the booster plate. Return to step four.

[0051] The verification of the booster guide vane includes the actual cooling air consumption of the booster guide vane. Average wall temperature , maximum wall temperature and internal pressure ratio wait.

[0052] The cooling design method for the afterburner guide plate in the afterburner chamber of an aero-engine disclosed in the above embodiments is based on the actual situation that the temperature distribution on the afterburner guide plate is uneven, the pressure distribution is different, and the flow rate of the outer bypass cooling gas is limited. The cooling area on the afterburner guide plate is divided into multiple cooling elements for precise cooling design, which can improve the wall temperature gradient on the afterburner guide plate, reduce the number of iterations, and has high efficiency.

[0053] The technical solution of this 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 this application is obviously not limited to these specific embodiments. Without departing from the principles of this 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 all fall within the scope of protection of this application.

Claims

1. A method for cooling design of a thrust nozzle in a turbofan engine afterburner, characterized in that, Comprising: Step one, determine the cooling area of the force guide; Step two, divide the cooling area into multiple cooling elements; Step three, with thermal-solid coupling three-dimensional simulation, calculate the heat transfer characteristic parameters of each cooling element under typical working state points, including the actual flow of each cooling element under the condition of opening cooling hole , blowing ratio of cooling gas jet to main flow , static pressure of cooling hole corresponding position in each cooling element under the condition of not opening cooling hole , wall temperature ; Step four, preliminary determination of the total amount of cooling gas for the force guiding vane , based on the static pressure of the cooling hole corresponding position in each cooling element without cooling hole , wall temperature , calculate the required amount of cooling gas for each cooling element ; Step five, the amount of cooling gas required for each cooling element , and the actual flow of single hole in the cooling element , the cooling hole area is calculated , and the total number of cooling holes is calculated , the opening rate ; Step 6: Based on the total number of cooling holes in each cooling element Opening ratio Determine the axial spacing of the cooling holes and radial spacing ; Step 7: Based on the axial spacing of the cooling holes of each cooling element and radial spacing Opening ratio Aperture And the ratio of cooling air jet to mainstream airflow. The overall film cooling efficiency was calculated. ; Step eight, calculating the wall temperature of each cooling element based on the collective film cooling effectiveness of the respective cooling element and hot gas side temperature of the plenum strut , cold gas side temperature , calculating the wall temperature of each cooling element ; Step nine, judge whether the wall temperature of each cooling element meets the average wall temperature requirement of the thrust vectoring vane , if not, adjust the total amount of cooling air of the thrust vectoring vane, and return to step four , if not, adjust the total amount of cooling air of the thrust vectoring vane, and return to step four , if not, adjust the total amount of cooling air of the thrust vectoring vane, and return to step four , if not, adjust the total amount of cooling air of the thrust vectoring vane, and return to step four 2. The method according to claim 1, wherein, Step five has: ； Wherein, The area for cooling the cell.

3. The method according to claim 1, wherein, Step eight has: 。 4. The method of cooling the struts of a turbine nozzle of a turbine augmentor of a gas turbine engine according to claim 1, wherein, Also comprising: Step ten, check the force guide vane with thermal solid coupling three-dimensional simulation, if the check is not satisfied, the total amount of cooling gas of the force guide vane is adjusted , return to step four.

5. The method according to claim 4, wherein, In step ten, the content of checking the afterburner guide vane includes the actual amount of cooling gas of the afterburner guide vane , the average wall temperature , the maximum wall temperature , and the ratio of the outer and inner pressure .

Images