Invention Grant
- Patent Title: Turbine stage shroud segment
- Patent Title (中): 涡轮级护罩段
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Application No.: US13177151Application Date: 2011-07-06
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Publication No.: US08714918B2Publication Date: 2014-05-06
- Inventor: Ian Tibbott , Peter Ireland , Anthony J Rawlinson , Lynne H Turner
- Applicant: Ian Tibbott , Peter Ireland , Anthony J Rawlinson , Lynne H Turner
- Applicant Address: GB London
- Assignee: Rolls-Royce PLC
- Current Assignee: Rolls-Royce PLC
- Current Assignee Address: GB London
- Agency: Oliff PLC
- Priority: GB1012783.5 20100730
- Main IPC: F01D11/10
- IPC: F01D11/10

Abstract:
A shroud segment for a turbine stage of a gas turbine engine forms an endwall for the working gas annulus of the stage. The segment also provides a close clearance to the tips of a row of turbine blades which sweep across the segment. In use a leakage flow of the working gas passes through the clearance gap between the blade tips and the segment. The segment has a plurality of cooling holes and respective air feed passages for the cooling holes. The cooling holes are distributed over that part of the gas-washed surface of the segment which is swept by the blade tips. The cooling holes deliver, in use, cooling air which spreads over the gas-washed surface. The feed passages are configured such that the delivered air opposes the leakage flow of the working gas.
Public/Granted literature
- US20120027576A1 TURBINE STAGE SHROUD SEGMENT Public/Granted day:2012-02-02
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