GAS TURBINE ENGINE ROTOR BLADING SEALING DEVICE
Assignee
SOCIETE NATIONALED ETUDE ET DE CONSTRUCTION DE MOTEURS D AVIATION S.N.E.C.M.A., , FRANCE
Filed
Dec 30, 1983
Granted
Jan 14, 1997
Location
SAINTRY SUR SEI FR
Abstract
The disclosed invention relates to a sealing device for the rotor blades of a gas turbine engine which permits real time adjustment to be made of the clearances between the rotor blade tips and the sealing structure. The sealing shroud around the turbine wheel is formed of sectors, each sector being attached to a monolithic short response time ring and a monolithic long response time ring. Ventilating air from upstream of the turbine wheel is directed onto the rings such that the sectors are caused to radially expand or contract in compliance with the expansion or contraction of the tips of the rotor blades during stabilized and transient engine operational modes. A small positive clearance between the sealing sectors and the blade tips is maintained throughout the range of the engine's operation.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Sep 24, 1985
Rescinded
Oct 27, 1995
Duration
10 years, 1 month
Inventor
- 1GERARD E. A. JOURDAIN
Record Details
- Patent number
- US 5593278
- Application
- 06568223
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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