Abstract: In a gas turbine engine bladed disk (36) positioned between rotor disk (14) and combustor (16). Bladed disk (36) is mounted for rotation together with rotor disk (14) and has blades (38) projecting toward inlet portion (20) of combustor (16). The bladed disk has openings (40) between blades (38) for establishing communication between source of compressed fluid (12) and turbine blades (15). Seals (46, 48) are provided between bladed disk (36) and casing (10).
Abstract: In a gas turbine engine in which bearings (18, 30) of turbine (12) and compressor turbine (22) and exhaust duct (32) of compressor turbine (22) are attached to external annular wall (46) of heat exchanger (44). External annular wall (46) of heat exchanger (44) has heat insulation layer (48) on the inside surface. The engine has cooling device (94) for cooling external annular wall (46) of heat exchanger (44) on the side opposite to heat insulating layer (48).
Type:
Grant
Filed:
March 11, 1999
Date of Patent:
February 20, 2001
Assignee:
ALM Development, Inc.
Inventors:
Anatoly Rakhmailov, Valentin Yaishnikov, Mikhail Kolotilenko, Oleg Rakhmailov, Igor Drozd, Martin Kalin