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Gas turbine aerofoil trailing edge

A gas turbine and airfoil technology, applied in climate sustainability, air transportation, engine functions, etc., can solve problems such as oxidation, limiting cooling efficiency of cooling flow, etc.

Inactive Publication Date: 2017-08-18
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] However, with a cutback design there is still a risk that the cooling flow lifts from the trailing edge before reaching the end of the airfoil thereby limiting the cooling efficiency of the cooling flow
This may cause the temperature to increase along the trailing edge to a value that may cause a portion of the trailing edge to oxidize away

Method used

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  • Gas turbine aerofoil trailing edge
  • Gas turbine aerofoil trailing edge
  • Gas turbine aerofoil trailing edge

Examples

Experimental program
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Embodiment Construction

[0039] figure 1 An example of gas turbine engine 10 is shown in cross-section. Gas turbine engine 10 includes an inlet 12 , a compressor section 14 , a combustor section 16 , and a turbine section 18 in a flow sequence generally arranged in a flow sequence and generally in the direction of a longitudinal or rotational axis X . Gas turbine engine 10 further includes a shaft 22 rotatable about an axis of rotation 20 and extending longitudinally through gas turbine engine 10 . Shaft 22 drivingly connects turbine section 18 to compressor section 12 .

[0040]In operation of gas turbine engine 10 , air 24 drawn through air inlet 12 is compressed by compressor section 12 and delivered to combustion or combustor section 16 . Compressor section 12 includes a plurality of stages including a plurality of compressor guide vanes 46 attached to a stator of compressor section 12 and a plurality of rotor compressor blades attached to shaft 22 downstream of vanes 46 48.

[0041] The combu...

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PUM

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Abstract

A turbine aerofoil (1) comprises: - a leading edge (3), - a trailing edge (5), - an exterior surface including a suction side (7) and a pressure side (9), - at least an internal cavity (11A-11D) for forming a cooling circuit comprising cooling slots (60, 61, 62) between the suction side (7) and the pressure side (9), wherein the aerofoil includes a first trailing portion (51) along the trailing edge (5) where both the suction side (7) and the pressure side (9) extend from the leading edge (3) up to the trailing edge (5) in order that the first cooling slot (61) is formed at the trailing edge (5), and at least a second trailing portion (51, 52) where the suction side (7) extends from the leading edge (3) up to the trailing edge (5) and the pressure side (9) extends from the leading edge (3) up to a cut-back edge (4) distanced from the trailing edge (5), in order that at least a second cooling slot (61, 62) is provided at the cut-back edge (4).

Description

technical field [0001] The present invention relates to gas turbine airfoils, and more particularly to gas turbine airfoil trailing edges provided with cooling slots. Background technique [0002] In a gas turbine engine, air is pressurized in a compressor and mixed with fuel in a combustor for generating hot combustion gases. The hot gas is then channeled toward a gas turbine that converts the energy from the hot gas into work for powering a compressor and other devices that convert power, such as those found in typical aircraft turbofan engine applications Upstream fans or generators in power generation applications. [0003] The gas turbine stage includes a stationary turbine nozzle having rows of hollow fins that channel combustion gases into corresponding rows of rotor blades extending radially outward from a supporting rotor disk. The vanes and blades may have corresponding hollow airfoils. Airfoils can be designed and manufactured hollow in order to save weight, ch...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/187F05D2240/304F05D2240/122F05D2240/126F05D2260/941F05D2260/202Y02T50/60F01D5/186F01D9/02F01D25/12F05D2220/32F05D2240/121F05D2240/303
Inventor L·S·王
Owner SIEMENS AG