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Turbine blade with contoured tip shroud

A technology for moving blades and turbine engines, applied in blade support elements, engine elements, engine manufacturing, etc., can solve problems such as reducing stage efficiency and increasing aerodynamic losses, reducing costs and complexity, improving aerodynamic performance, and improving control. Effect

Inactive Publication Date: 2018-03-27
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Removing material by scalloping increases aerodynamic losses, reducing stage efficiency

Method used

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  • Turbine blade with contoured tip shroud
  • Turbine blade with contoured tip shroud
  • Turbine blade with contoured tip shroud

Examples

Experimental program
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Embodiment Construction

[0027] In the following detailed description of the preferred embodiments, reference is made to the accompanying drawings constituting a part of this document, and specific embodiments in which the present invention can be implemented are shown in an illustrative and non-limiting manner. It should be understood that other embodiments may be used, and changes may be made without departing from the spirit and scope of the present invention.

[0028] A gas turbine engine may include a compressor section, a combustion chamber, and a turbine section. The compressor section compresses the surrounding air. The combustion chamber combines compressed air with fuel and ignites the mixture to produce combustion products containing hot gases that form a working fluid. The working fluid travels to the turbine section. Circumferential rows of stationary blades and moving blades are located in the turbine section, and the moving blades are coupled to the rotor. Each pair of stationary blade ...

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PUM

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Abstract

A turbine blade (10) includes a generally elongated airfoil (32) extending span-wise along a radial direction, and a circumferentially extending shroud (70) coupled to a radially outer tip (24) of theairfoil (32). The shroud (70) includes an upstream edge (72) and a downstream edge (74) spaced apart axially. The shroud (70) further includes a radially inner surface (76) adjoining the tip (24) ofthe airfoil (32) and a radially outer surface (78) generally opposite to the radially inner surface (76). The radially inner surface (76) and the radially outer surface (78) are connected at the upstream edge (72) and at the downstream edge (74). In circumferential cross-section, the shroud (70) has a shape of an aerodynamic lifting body (60, 62) defined by a contour of the radially inner surface(76) and that of the radially outer surface (78). The shape of the aerodynamic lifting body (60, 62) is configured such that a radially inward acting lift force (L) is exerted on the shroud (70) by agenerally axial fluid flow (F) over the shroud (70).

Description

Technical field [0001] The present invention relates generally to turbine moving blades, and in particular to turbine moving blades with tip shrouds. Background technique [0002] Generally, a gas turbine engine includes a compressor for compressing air, a combustion chamber for mixing compressed air with fuel and igniting the mixture, and a turbine moving blade assembly for generating power. The combustion chamber often operates at high temperatures that may exceed 2500 degrees Fahrenheit. The typical turbine combustor structure exposes the turbine rotor blade assembly to such high temperatures. Therefore, turbine rotor blades must be made of materials that can withstand such high temperatures. [0003] The turbine rotor blade is formed by a root portion coupled to the rotor disc and an elongated airfoil extending outward from the platform coupled to the root portion. The moving blade is usually composed of a tip, a leading edge and a trailing edge opposite to the root. The ti...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/22
CPCF01D5/225F01D5/143F01D5/147F01D5/28F01D11/127F05D2250/71
Inventor 小尼古拉斯·F·马丁安德鲁·S·洛豪斯
Owner SIEMENS AG