F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 5/22 (2006.01) F01D 9/02 (2006.01) F02C 3/04 (2006.01) F04D 29/54 (2006.01) F04D 29/64 (2006.01)
Patent
CA 2678510
The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades (11, 12; 12, 13; 13, 14) are permanently connected to each other within each guide blade segment (10) of at least one guide blade ring on opposing surfaces positioned radially outward, whereas the same are not connected to each other on opposing surfaces positioned radially inward.
L'invention concerne un compresseur, en particulier un compresseur à haute pression, une turbine à gaz, en particulier un moteur à turbine à gaz aérodynamique, comprenant au moins une couronne d'aubes mobiles côté moteur et au moins une couronne d'aubes fixes côté stator, la ou les couronnes d'aubes fixes étant constituée(s) de plusieurs segments d'aubes fixes, et chaque segment d'aube fixe étant constitué de plusieurs aubes individuelles. Selon l'invention, dans chaque segment d'aube fixe (10) d'au moins une couronne d'aubes fixes des aubes individuelles (11, 12; 12, 13; 13, 14) adjacentes sont reliées de manière durable au niveau de surfaces opposées radialement externes mais pas au niveau de surfaces opposées radialement internes.
Liebl Christian
Lottprein Hans-Georg
Marks & Clerk
Mtu Aero Engines Gmbh
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