COOLING OF GAS TURBINE SHROUD RINGS
Assignee
ROLLS-ROYCE LIMITED, A BRITISH COMPANY
Filed
Apr 30, 1984
Granted
Jan 12, 1993
Location
DERBY GB
Abstract
A gas turbine engine is provided with an annular array of rotor blades which are surrounded by a shroud ring. The shroud ring includes a number of adjacent heat pipes which are of the variable conductance type. The heat pipes each have a portion which is externally of the shroud ring which portion is in turn divided into two parts. The first part is exposed to a flow of cooling air while the second part contains a buffer which operationally varies the conductance of the heat pipe, in accordance with the temperature of air which is tapped from the high pressure compressor of the engine. This serves to ensure that the shroud ring remains substantially isothermal and provides control over the clearance between the tips of the rotary blades and the shroud ring through thermal control of the shroud ring.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 19, 1986
Rescinded
Aug 14, 1991
Duration
5 years, 2 months
Inventor
- 1PETER A. DAMIRAL
Record Details
- Patent number
- US 5178514
- Application
- 06633265
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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