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Grid seam air film cooling structure with bobbin type turbulent flow columns and double-fillet outlet

A technology of spoiler columns and grids, applied in the direction of blade support components, engine components, machines/engines, etc., can solve the problems of weak span-wise coverage and inability to form air film coverage near the wall, and achieve the elimination of low-speed backflow vortices , enhance the effect of flow direction coverage, and improve the effect of heat exchange intensity

Inactive Publication Date: 2019-08-02
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In 2003, C. Yuen et al. (Filmcooling characteristics of rows of round holes at various streamwise angles in a crossflow: Part I. Effectiveness. International Journal of Heat & Mass Transfer, 2003, 46(2), 221-235.) found in subsequent studies The spanwise coverage of the cylindrical hole jet is weak, and the jet gas is raised so that the near wall cannot form an effective gas film coverage

Method used

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  • Grid seam air film cooling structure with bobbin type turbulent flow columns and double-fillet outlet
  • Grid seam air film cooling structure with bobbin type turbulent flow columns and double-fillet outlet
  • Grid seam air film cooling structure with bobbin type turbulent flow columns and double-fillet outlet

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Effect test

Embodiment 1

[0028] This embodiment is applied to a turbine guide blade; the suction surface of the turbine blade is close to the leading edge of the blade, and a spool-type spoiler column and a grid slit structure 5 with the suction surface close to the leading edge of the blade are arranged, and air is supplied by the inner cooling channel 4; In the two-dimensional grid slit structure formed by the lip plate 1 and the bottom plate 3, a bobbin-type spoiler column 2 is arranged, and the bobbin-type spoiler column 2 is arranged in a cross row, and the outlet of the grid slit adopts a double round structure. The outer profile of the lip plate 1 and the bottom plate 3 in the grid slit film cooling structure with spool-type spoiler columns and double rounded outlets are flush. The diameter D of the outer disc of the spool spoiler column is 0.6mm; the diameter d of the spool spoiler 2 waist plate is 0.4mm; the radius of the rounding radius R of the outer disc of the spool spoiler 2 is 0.1d , The...

Embodiment 2

[0030] This embodiment is a grid slit film cooling structure with spool spoiler and double rounded outlets applied to the turbine guide blades. The pressure surface of the turbine blade is arranged with a spool-type spoiler column and a grid slit structure 7 on the pressure surface, and air is supplied by the internal cooling channel 6. Among them, the two-dimensional grid slit structure formed by the lip plate 1 and the bottom plate 3 is provided with a wire shaft spoiler column 2, which is arranged in a row, and the outlet part of the grid slit adopts a double round structure. The outer profile of the lip plate and the bottom plate in the grid slit film cooling structure with spool-type spoiler column and double rounded outlets are flush. The diameter D of the outer disc of the spool spoiler 2 is 0.9mm, the diameter d of the waist disc of the spool spoiler 2 is 0.6mm, and the rounding radius R of the outer disc of the spool spoiler 2 is 0.12. d, the value of the round radius...

Embodiment 3

[0032] This embodiment is a grid slit film cooling structure with spool spoiler and double rounded outlets applied to the turbine guide blades. Arranged on the pressure surface of the turbine blade near the leading edge of the blade with a spool-shaped spoiler column and a grid slit structure 9 with the pressure surface near the trailing edge of the blade, air is supplied by the internal cooling channel 8; among them, the two formed by the lip plate 1 and the bottom plate 3 The wire shaft spoiler column 2 is arranged in the dimensional grid slit structure, and the spool spoiler column 2 is arranged in a cross row, and the outlet of the grid slit is a double rounded structure. The lip plate 1 in the grid slit film cooling structure is flush with the outer profile of the bottom plate 3. The diameter D of the spool spoiler 2 outer disc is 1mm, the diameter d of the spool spoiler 2 waist disc is 0.4mm, and the round radius R of the outer disc of the spool spoiler 2 is 0.12d. , The...

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Abstract

The invention discloses a grid seam air film cooling structure with bobbin type turbulent flow columns and a double-fillet outlet. The structure is composed of a lip plate, the bobbin type turbulent flow columns and a bottom plate. A two-dimensional seam structure is formed by the lip plate and the bottom plate, and the bobbin type turbulent flow columns are arranged in the two-dimensional seam structure to be used for guiding flow and strengthening the structure. The bobbin type turbulent flow columns adopt a sequential arrangement or cross arrangement manner. The grid seam outlet is of a double-fillet structure. The outer molded surfaces of the lip plate and the bottom plate are flushed, and the influence on blade pneumatic performance is reduced. By means of the bobbin type turbulent flow columns, low-speed backflow vortexes behind the turbulent flow columns are eliminated, and the heat exchange strength in a grid seam is effectively improved. By means of the bobbin type turbulent flow columns, the heat exchange area in the grid seam is greatly increased, and heat exchange in the grid seam is enhanced. Pneumatic losses of cold air in the seam are effectively reduced, and the flowing coverage effect f cold air is enhanced. The grid seam outlet is of the double-fillet structure, cold air cannot be directly injected into main flow after leaving the grid seam and is effectivelyattached to the area nearby the wall face, and the attachment capacity of an air film behind the seam is enhanced.

Description

Technical field [0001] The invention relates to the technical field of gas turbine blade cooling, in particular to a grid slit gas film cooling structure with a bobbin-type spoiler column and double rounded outlets. Background technique [0002] With the improvement of gas turbine performance, the turbine inlet temperature continues to increase. The inlet temperature of some advanced engines has reached more than 2000k. Therefore, effective cooling measures must be used to protect the turbine blades to avoid high temperature corrosion and damage to the blades. . Film cooling is one of the typical cooling methods used on blades. Film cooling is to inject a low-temperature airflow along a tangent line or at a certain angle near the wall surface to isolate the high-temperature gas from the wall surface to achieve cooling and protection of the heated wall surface. [0003] Cylindrical air film hole is the earliest air film hole type. A large number of domestic and foreign scholars ha...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/186
Inventor 朱惠人张博伦姚春意刘存良
Owner NORTHWESTERN POLYTECHNICAL UNIV