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Turboengine blading member

A technology for turbine engines, components, applied in the direction of engine elements, machines/engines, support elements for blades, etc.

Active Publication Date: 2017-06-20
ANSALDO ENERGIA IP UK LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, due to different cooling and thermal loads of the platform and airfoils, additional stresses can be induced due to thermal expansion inconsistencies

Method used

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  • Turboengine blading member
  • Turboengine blading member
  • Turboengine blading member

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0049] figure 1A general side view of a turbine engine blade arrangement component 1 as described herein is shown. The blade means 1 comprises an airfoil 2 and a platform 31 arranged at the base of the airfoil 2 . The airfoil 2 comprises a leading edge 21 and a trailing edge 22 . Thus, the hot working fluid flow 4 is expected to flow along the airfoil 2 from the leading edge 21 to the trailing edge 22 and along the working fluid exposed surface 32 of the platform. Typically, attachment features 34 are provided at the coolant side 33 of the platform for attaching the blading member 1 to the rotor or stator. The attachment features are shown in schematic depiction only and are well known features to those skilled in the art. Typically, coolant is provided on the coolant side 33 at the platform 31 during operation of the engine. Said coolant can be used in a manner known per se to cool the platform, but, as is well known to those skilled in the art, can also be directed into ...

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PUM

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Abstract

A turboengine blading member (1) is disclosed. The blading member comprises at least one airfoil (2) and at least one platform (31) provided at at least one of a base and a tip of the airfoil (2). The airfoil (2) comprising a profile body (23), a leading edge (21) provided at a first side of the profile body (23), and a trailing edge section (24) extending from a second side of the profile body (23) and opposite the leading edge (21). The profile body (23) is connected to the at least one platform (31). The trailing edge section (24) cantilevers from the profile body (23) and is provided without connection to the platform (31).

Description

technical field [0001] The present disclosure relates to a turbine engine blade arrangement member as set forth in claim 1 and also to an airfoil member for a turbine engine blade arrangement member. Background technique [0002] A turbine engine blade assembly includes at least one airfoil and a platform. The platform may be provided at only one end of the airfoil, ie at the base or tip, so that the airfoil extends from the platform along its span. In other embodiments, so-called shrouded blades, the platforms are arranged at both ends of the airfoil such that the airfoil extends along its span between the two platforms. Furthermore, the blade means may comprise a plurality of at least two airfoils such that two or more airfoils respectively extend from one platform or between two platforms. [0003] The blading member may be provided on the turbine engine rotor as a rotating blading member, or as part of the turbine engine stator as a stationary blade member which may al...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/14F01D5/18
CPCF01D5/147F01D5/18F05D2240/304F01D5/145F01D9/042F05D2230/642F05D2240/122F05D2240/81F05D2240/80F01D5/187F01D5/3015F05D2220/32F05D2240/24F05D2240/303F05D2240/305F05D2240/306F05D2240/307
Inventor H.布兰德尔J.克吕克尔斯T.齐雷尔
Owner ANSALDO ENERGIA IP UK LTD