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CN-121997476-A - Turbine blade lower edge plate optimization design method and system, turbine stator and lower edge plate

CN121997476ACN 121997476 ACN121997476 ACN 121997476ACN-121997476-A

Abstract

A turbine blade lower edge plate optimization design method and system, a turbine stator and a lower edge plate. The optimal design method comprises the steps of S1, obtaining seal performance parameters through simulation calculation of a model flow field, S2, setting an axial extension length design range of a lower edge plate exhaust edge relative to a turbine blade tail edge, obtaining a fillet radius design range of the lower edge plate exhaust edge, S3, obtaining multiple groups of axial extension length-fillet radius data in the axial extension length design range and the fillet radius design range by using a test design method and taking the axial extension length and the fillet radius as optimization variables, S4, obtaining multiple groups of seal performance parameters corresponding to the multiple groups of axial extension length-fillet radius data, S5, obtaining regression relations between the seal performance parameters, the fillet radius and the axial extension length according to the multiple groups of seal performance parameters, and S6, obtaining optimal solutions of the fillet radius and the axial extension length according to the regression relations.

Inventors

  • SHEN XIAOHUI
  • ZHAO LEI
  • MA GUOJUN

Assignees

  • 中国航发商用航空发动机有限责任公司

Dates

Publication Date
20260508
Application Date
20241106

Claims (10)

  1. 1. The turbine blade lower edge plate optimizing design method is characterized by comprising the following steps of: S1, performing flow field simulation calculation on a model of a lower edge plate with turbine blades to obtain sealing performance expression parameters; S2, setting an exhaust edge of the lower edge plate to axially protrude from the tail edge of the turbine blade and obtain an axial protruding length design range for the model, and setting a round angle on the exhaust edge of the lower edge plate and obtaining a round angle radius design range; s3, setting the axial extension and the fillet radius as optimization variables, setting the sealing performance parameters of the step S1 as optimization targets, and obtaining a plurality of groups of axial extension-fillet radius data in the axial extension design range and the fillet radius design range of the step S2 by using a test design method; S4, performing flow field simulation calculation on the model provided with the multiple groups of axial extension length-fillet radius data in the step S3 to obtain multiple groups of sealing performance parameters corresponding to the multiple groups of axial extension length-fillet radius data; S5, obtaining a regression relation between the sealing performance parameters, the fillet radius and the axial extension according to the plurality of groups of sealing performance parameters corresponding to the plurality of groups of axial extension-fillet radius data in the step S4, and And S6, obtaining an optimal solution of the fillet radius and the axial extension according to the regression relation.
  2. 2. The optimization design method according to claim 1, wherein: The sealing performance parameters of the step S1 include a fuel gas backflow rate, a disk cavity temperature and turbine stage efficiency.
  3. 3. The optimization design method according to claim 1, wherein: the model of step S1 further comprises a turbine disc.
  4. 4. The optimization design method according to claim 1, wherein the step S1 further comprises: a mesh of the model is generated, wherein the model at the underside of one third or one half of the leaf height generates an unstructured mesh.
  5. 5. The optimization design method according to claim 4, wherein the step S1 further comprises: Setting the grid density of the unstructured grid to be 0.001, and setting the minimum grid quality of the unstructured grid to be greater than 0.1.
  6. 6. The optimization design method according to claim 1, wherein the step S2 further comprises: The design range of the axial extension is set to be 0-2 mm, and the design range of the fillet radius is set to be 0.5-3 mm.
  7. 7. The optimization design method according to claim 1, wherein the step S3 further comprises: Five sets of the axial elongation-the fillet radius data are obtained by a latin hypercube optimization algorithm.
  8. 8. A turbine blade lower edge panel optimization design system for performing the turbine blade lower edge panel optimization design method as claimed in any one of claims 1 to 7.
  9. 9. The utility model provides a turbine stator blade lower margin board which characterized in that: the exhaust edge of the lower edge plate is configured to axially protrude from the trailing edge of the turbine stationary blade, the length of the axial protrusion is 1.5 mm, the lower edge plate is provided with a round angle on the exhaust edge, and the radius of the round angle is 0.5 mm.
  10. 10. A turbine stator, includes turbine stator blade and lower edge plate, its characterized in that: the exhaust edge of the lower edge plate axially protrudes from the tail edge of the turbine stationary blade, the axial protruding length is 1.5 mm, the lower edge plate is provided with a round angle on the exhaust edge, and the radius of the round angle is 0.5 mm.

Description

Turbine blade lower edge plate optimization design method and system, turbine stator and lower edge plate Technical Field The invention relates to a gas turbine design, in particular to a turbine blade lower edge plate optimal design method, a turbine blade lower edge plate optimal design system, a turbine stationary blade lower edge plate and a turbine stator. Background The gas turbine is widely applied to the national economy field such as energy power, aerospace and the like and the national defense and military field. The turbine is developed towards high parameters, high performance and high reliability, the temperature before the turbine is continuously increased, the sealing leakage between the stages is caused, the fuel gas flows backward, the temperature of a disk cavity is increased, the temperature of the turbine disk is over-high, and the service life of the turbine disk is reduced. In order to improve sealing performance and prevent fuel gas from flowing backward, the main flow energy loss is increased by increasing the inter-stage sealing cold air quantity, the turbine efficiency is reduced, and the rub risk is increased by arranging the grate sealing structure. Disclosure of Invention The invention aims to provide a turbine blade lower edge plate optimal design method and system, a turbine stator and a lower edge plate, which are used for improving the inter-stage sealing performance. According to the embodiment of the invention, the optimal design method comprises the steps of S1, S2, S3, S4, S5 and S6, wherein the step S1 is used for carrying out flow field simulation calculation on a model of a lower edge plate with a turbine blade to obtain sealing performance parameters, the step S2 is used for setting an exhaust edge axial extension of the lower edge plate on a trailing edge of the turbine blade and obtaining an axial extension design range, a round angle is set on the exhaust edge of the lower edge plate and obtaining a round angle radius design range, the step S3 is used for setting the axial extension and the round angle radius as optimization variables, the sealing performance parameters of the step S1 are set to be optimization targets, a plurality of sets of axial extension-round angle radius data are obtained in the axial extension design range and the round angle radius design range of the step S2, the step S4 is used for setting the axial extension-round angle performance parameters to obtain the corresponding regression performance parameters of the axial extension-round angle performance parameters, and the step S4 is used for carrying out the simulation calculation on the plurality of sets of the axial extension-round angle performance parameters and the round angle performance parameters to obtain the corresponding to the axial extension performance parameters of the step S4. In one or more embodiments, the seal performance parameters of step S1 include gas backflow rate, disk cavity temperature, and turbine stage efficiency. In one or more embodiments, the model of step S1 further includes a turbine disk. In one or more embodiments, the step S1 further comprises generating a grid of the model, wherein the model located on the underside of one third or one half of the leaf height generates an unstructured grid. In one or more embodiments, the step S1 further includes setting a mesh density of the unstructured mesh to 0.001, and setting a minimum mesh mass of the unstructured mesh to be greater than 0.1. In one or more embodiments, the step S2 further includes setting the design range of the axial protrusion length to be 0mm to 2mm, and setting the design range of the fillet radius to be 0.5 mm to 3 mm. In one or more embodiments, the step S3 further includes obtaining five sets of the axial elongation-the fillet radius data by a latin hypercube optimization algorithm. In a second aspect, the present invention provides a turbine blade lower edge panel optimization design system, according to an embodiment of the present invention, the optimization design system is used to execute the above-mentioned turbine blade lower edge panel optimization design method. In a third aspect, the present invention provides a turbine vane lower edge plate, according to an embodiment of the present invention, an exhaust edge of the lower edge plate is configured to axially protrude from a trailing edge of a turbine vane, and the axial protruding length is 1.5 millimeters, the lower edge plate is provided with a fillet at the exhaust edge, and the radius of the fillet is 0.5 millimeters. In a fourth aspect, the present invention provides a turbine stator, according to an embodiment of the present invention, the turbine stator includes a turbine vane and a lower rim plate, an exhaust edge of the lower rim plate axially protrudes from a trailing edge of the turbine vane, and the axial protruding length is 1.5 mm, the lower rim plate is provided with a fillet at the exhaust edge, and a radius of