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Cooling solutions for turbine blades of gas turbines

A technology for turbine blades and gas turbines, which can be used in blade support elements, engine manufacturing, machine/engine, etc., and can solve problems such as expensive manufacturing.

Active Publication Date: 2020-06-05
ANSALDO ENERGIA SWITZERLAND AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] Solution (3) avoids the disadvantages of solutions (1) and (2), but is expensive in terms of manufacture (casting) and still does not provide an optimal angle between the cooling jet and the inner surface of the airfoil wall

Method used

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  • Cooling solutions for turbine blades of gas turbines
  • Cooling solutions for turbine blades of gas turbines
  • Cooling solutions for turbine blades of gas turbines

Examples

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Embodiment Construction

[0059] The present invention provides an enhanced cooling heat transfer at the leading edge region of a turbine blade applied by means of an impingement cooling scheme, thereby using the cooling medium (eg air) heat capacity.

[0060] figure 2 The rationale for having a leading edge cooling scheme according to an embodiment of the invention is shown figure 1 A cross-section of the airfoil 29 of the rotating turbine blade 12 . The airfoil 29 has a leading edge 24 and a trailing edge 25 . The airfoil 29 also has a suction side 26 and a pressure side 27 . Chord 40 characterizes the profile of airfoil 29 . The hollow interiors of the airfoils 29 are each divided into a first cavity 15 and a second cavity 17 by means of an internal web 16 . The cooling medium flows from the root of the blade 12 in the radial direction R (see Figure 5) into the first chamber 15.

[0061] The inner webs 16 are each provided with two rows of cooling medium supply holes 18 and 19, through whic...

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Abstract

A turbine blade (12) of a gas turbine includes a radially extending airfoil (29) having suction sides ( 26) and the pressure side (27), wherein the leading edge is cooled by means of impingement cooling with rows of radially distributed jets of cooling medium impinging on the inner side of the leading edge, and wherein the rows of radially distributed The jet of the airfoil is generated at the inner web (16), which divides the hollow interior of the airfoil into a first cavity (15) and a second cavity (17), wherein the second cavity is arranged at the leading edge. Enhanced cooling is achieved by the inner web (16) comprising two rows of radially distributed cooling medium supply holes (18, 19), through which the cooling medium enters the second cavity (17) in the form of impinging jets, Wherein the cooling medium supply holes are oriented such that the direction of the jets of one row crosses the direction of the jets of the other row.

Description

technical field [0001] The present invention relates to gas turbine technology. It relates to a turbine blade of a gas turbine according to the preamble of claim 1 . Background technique [0002] Figure 6 An example of a turbine in the form of a gas turbine of the applicant's GT24 or GT26 type is shown in a perspective view. Figure 6 The gas turbine 30 comprises a rotor 31 rotating about a machine axis and surrounded by an (inner) casing 32 . Arranged along the machine axis, the gas turbine 30 includes an intake 33, a compressor 34, a first combustor 35, a first high pressure (HP) turbine 36, a second combustor 37, a second low pressure (LP) turbine 38 and an exhaust Exit 39. [0003] In operation, air enters the machine via inlet air 33, is compressed by a compressor 34, and is fed to a first burner 35 for burning fuel. The resulting hot gases drive HP turbine 36 . While it still contains air, it is then reheated by means of a second burner 37 where fuel is injected i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18
CPCF01D5/187F05D2240/303F05D2250/38F05D2260/201F05D2220/32F05D2250/71
Inventor S.斯楚金
Owner ANSALDO ENERGIA SWITZERLAND AG