F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 11/10 (2006.01) F01D 11/12 (2006.01)
Patent
CA 2657190
A gas turbine is disclosed, with at least one compressor, at least one combustion chamber, and at least one turbine, wherein the, or each, compressor and/or the, or each, turbine has a rotor comprising guide vanes (12) enclosed by a static housing (13), and wherein an inlet covering (15) is assigned to the housing. The gas turbine comprises at least one channel (19) in order to apply a pressure prevailing on the high pressure side of the guide vanes (12) of a rotor to a low pressure side of same, in the region of a gap (17) between the radially external ends (16) of the guide vanes (12) and the housing (13), and thus to eliminate a flow through the gap (17).
L'invention concerne une turbine à gaz dotée d'au moins un compresseur, d'au moins une chambre de combustion et d'au moins une turbine, le ou chaque compresseur et/ou la ou chaque turbine présentant un rotor comprenant des aubes mobiles (12) et entouré par un boîtier fixe (13) et une garniture d'admission (15) étant associée au boîtier. La turbine à gaz comprend au moins un canal (19) pour exercer une pression régnant sur le côté haute pression des ailettes mobiles (12) d'un rotor sur un côté basse pression de ces ailettes dans la zone d'un intervalle (17) entre les extrémités radiales extérieures (16) des ailettes mobiles (12) et le boîtier (13) et pour éliminer ainsi un courant traversant l'intervalle (17).
Dusel Karl-Heinz
Huttner Roland
Seitz Peter
Marks & Clerk
Mtu Aero Engines Gmbh
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