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Edge-blended hole structure used for air film cooling of turbine blades

A technology of film cooling and turbine blades, which is applied to the supporting components of blades, engine components, machines/engines, etc., can solve the problems of high cost and difficulty in processing special-shaped holes, achieve low cost, improve film cooling efficiency, and flow uniform effect

Inactive Publication Date: 2017-05-10
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to effectively improve the film cooling efficiency of the cylindrical hole shape, and overcome the disadvantages of difficulty in processing special-shaped holes and high cost in the prior art, the present invention proposes a rounded edge hole structure for film cooling of turbine blades

Method used

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  • Edge-blended hole structure used for air film cooling of turbine blades
  • Edge-blended hole structure used for air film cooling of turbine blades
  • Edge-blended hole structure used for air film cooling of turbine blades

Examples

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Embodiment 1

[0023] This embodiment is an edge-rounded hole structure applied to film cooling on a certain type of turbine blade. A pressure surface air film hole 1 is provided on the pressure surface of the blade, and a suction surface air film hole is provided on the suction surface of the blade. 2. The two ends of the air film hole 1 on the pressure side and the air film hole 2 on the suction side form the outlet and inlet of the airflow respectively, and communicate with the cooling channel 3 in the blade for air supply; wherein, the inclined cylindrical hole 4 in the flow direction is rounded at the outlet Enlarging and forming, the inlet cross section of the inclined cylindrical hole 4 is an ellipse, and the outlet cross section is an ellipse larger than the inlet cross section formed by edge rounding. The inclination angle of the flow direction of the inclined cylindrical hole 4 is α, the diameter of the inclined cylindrical hole is D, and the edge rounding radius is R.

[0024] The...

Embodiment 2

[0026] This embodiment is an edge-rounded hole structure applied to film cooling on a certain type of turbine blade. A pressure surface air film hole 1 is provided on the pressure surface of the blade, and a suction surface air film hole is provided on the suction surface of the blade. 2. The two ends of the air film hole 1 on the pressure side and the air film hole 2 on the suction side form the outlet and inlet of the airflow respectively, and communicate with the cooling channel 3 in the blade for air supply; wherein, the inclined cylindrical hole 4 in the flow direction is rounded at the outlet Enlarging and forming, the inlet cross section of the inclined cylindrical hole 4 is an ellipse, and the outlet cross section is an ellipse larger than the inlet cross section formed by edge rounding. The inclination angle of the flow direction of the inclined cylindrical hole 4 is α, the diameter of the inclined cylindrical hole is D, and the edge rounding radius is R.

[0027] The...

Embodiment 3

[0029] This embodiment is an edge-rounded hole structure applied to film cooling on a certain type of turbine blade. A pressure surface air film hole 1 is provided on the pressure surface of the blade, and a suction surface air film hole is provided on the suction surface of the blade. 2. The two ends of the air film hole 1 on the pressure side and the air film hole 2 on the suction side form the outlet and inlet of the airflow respectively, and communicate with the cooling channel 3 in the blade for air supply; wherein, the inclined cylindrical hole 4 in the flow direction is rounded at the outlet Enlarging and forming, the inlet cross section of the inclined cylindrical hole 4 is an ellipse, and the outlet cross section is an ellipse larger than the inlet cross section formed by edge rounding. The inclination angle of the flow direction of the inclined cylindrical hole 4 is α, the diameter of the inclined cylindrical hole is D, and the edge rounding radius is R.

[0030] The...

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Abstract

The invention discloses an edge-blended hole structure used for air film cooling of turbine blades. Edge-blending expansion-molding is conducted on an outlet of a single-hole-diameter oblique cylindrical hole, the section of an inlet of the oblique cylindrical hole is elliptical, and the section of the outlet is an ellipse which is formed through edge blending and greater than the section of the inlet. The included angle between an air film hole central line on each turbine blade and the surface of the blade is 35 degrees, the value of the ratio R / D of the edge-blending radius R to the diameter D of the oblique cylindrical hole is 0.11:0.33. Cold air jet flow in the edge-blended hole structure used for air film cooling of the turbine blades flows uniformly at the hole outlet, jet cold air covers a wide area spanwise, the cold air core is closer to the wall face, and the cooling effect is good; and the flow loss of the edge-blended hole is small, and the heat exchange coefficient of a heat exchange surface is smaller. The edge-blended hole structure used for air film cooling of the turbine blades has the characteristic of being easy, convenient and fast to machine. Due to the applicability of the edge-blended hole structure, the air film cooling efficiency can be improved, the working reliability of the turbine blades is improved, and the service lives of the turbine blades are prolonged.

Description

technical field [0001] The invention relates to the cooling technology of the turbine blades of gas turbines, in particular to a rounded edge hole structure for gas film cooling of the turbine blades. [0002] technical background [0003] With the rapid development of aero-engines, the turbine inlet temperature continues to increase, and the turbine inlet temperature of a first-stage engine with a thrust-to-weight ratio of 10 has reached 1900K-2000K, which has far exceeded the heat resistance limit of turbine blade materials. At present, film cooling technology is widely used in aero-engines to cool turbine blades. Air film cooling is a cooling technology applied to gas turbine blades. It means that the internal cooling air flows out through scattered holes or slots, forming a cold air film with a lower temperature near the surface of the blade, isolating the wall surface from high-temperature gas, and taking away part of it. The high-temperature gas or bright flame radiate...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/187
Inventor 朱惠人周申平魏建生陈大为
Owner NORTHWESTERN POLYTECHNICAL UNIV