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Assembly of blade and seal for blade pocket

A technology of seals and blades, applied in the field of rotor components, can solve problems such as improper installation of seals and affecting the efficiency of sealing action

Pending Publication Date: 2020-08-14
PRATT & WHITNEY CANADA CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, there is a risk that the seal may not fit properly and this may affect the efficiency of the sealing action

Method used

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  • Assembly of blade and seal for blade pocket
  • Assembly of blade and seal for blade pocket
  • Assembly of blade and seal for blade pocket

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0010] figure 1 Illustrated is a gas turbine engine 10 of the type preferably arranged for use in subsonic flight, which generally includes the following components in series communication, namely: a fan 12 through which ambient air is propelled; A compressor section 14; a combustor 16 in which compressed air is mixed with fuel and ignited to produce an annular flow of hot combustion gases; and a turbine section 18 for extracting energy from the combustion gases. One or more shafts 17 are in driving engagement with other rotating parts of engine 10 in compressor section 14 and turbine section 18 .

[0011] refer to figure 2 and image 3 , which partially illustrates an embodiment of a rotor assembly 20 for a gas turbine engine 10 . Rotor assembly 20 may be any suitable component of compressor section 14 or turbine section 18 that includes a rotor disk 30 (partially shown) and rotor blades 40 that revolve around axis 11( figure 1 ) of the axis 17 and rotates therewith. In...

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PUM

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Abstract

The invention relates to an assembly of a blade and a seal for a blade pocket. An assembly comprises a blade including a blade portion, a root portion and a platform portion between the blade portionand the root portion, the platform portion defining at least one cavity opened laterally. An abutment projects from a wall portion of the cavity at a trailing end of the blade. A seal is received in the cavity and positioned along a periphery of the cavity, the seal having a trailing edge abutting against the abutment.

Description

technical field [0001] This application relates to rotor assemblies of the type found in gas turbine engines, and more particularly to sealing such assemblies. Background technique [0002] A feather seal design is used to engage the blade recess cavity. These seals may be positioned along gaps extending between adjacent blade platforms. Such a seal may be in the form of an "inverted U" design with legs extending beyond the front and rear of the blade platform. These legs can be used to stop the seal from moving within the blade / disk cavity. Sealing efficiency relies on proper insertion of the seal into the cavity such that the seal contacts the surface of the cavity along the gap. Since these cavities may be asymmetrical from leading edge to trailing edge, the seal may also have an asymmetrical shape from front leg to rear leg (eg, longer rear leg). Therefore, there is a risk that the seal may not be installed properly and this may affect the efficiency of the sealing a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/30F01D11/00
CPCF01D5/30F01D11/006F01D5/147
Inventor L.桑扎利O.莱格扎奥尼
Owner PRATT & WHITNEY CANADA CORP