Back to results
US 9,004,852 B2Granted
Ventilation of a high-pressure turbine in a turbomachine
AssigneeSnecma
InventorsMathieu Dakowski, Fabrice Garin, Delphine Roussin-Leroux, Wilfried Schweblen
Life of this patent
Estimating the term…
Abstract
A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc and receives a ventilation air flow and of which the other is downstream of the disc, the upstream flange of the disc including a mechanism connecting to the upstream eternal cavity and the internal cavity for ventilating the hub of the disc.
Claims11
A high pressure turbine for a turbomachine, the turbine comprising:
- at least one bladed rotor disk including upstream and downstream annular flanges separating a radially inner annular cavity containing a hub of the disk from a first radially outer annular cavity and a second radially outer annular cavity, the first radially outer annular cavity being upstream from the disk, and the second radially outer annular cavity being downstream from the disk;
- and
- fluid injectors for providing from upstream a stream of air to the first radially outer annular cavity, the stream of air coming from a combustion chamber end,
- wherein:
- the radially inner annular cavity has a first portion extending upstream of said at least one bladed rotor disk, and a second portion extending downstream of said at least one bladed rotor disk,
- the upstream flange of the disk includes means for passing said stream of air from the first radially outer annular cavity to the first portion of the radially inner annular cavity,
- the radially inner annular cavity is delimited radially inwards by a cylindrical shroud or sheath having an upstream end fastened to a first component carrying the upstream flange of the disk, and having a downstream end fastened to a second component carrying the downstream flange of the disk, so that said stream of air passes from the first portion to the second portion of the radially inner annular cavity, and
- the downstream flange of the disk includes means for passing said stream of air from the second portion of the radially inner annular cavity to the second radially outer annular cavity.
5 more elements
A high pressure turbine for a turbomachine, the turbine comprising:
- at least one bladed rotor disk including upstream and downstream annular flanges separating a radially inner annular cavity containing a hub of the disk from a first radially outer cavity and a second radially outer annular cavity, the first radially outer annular cavity being upstream from the disk, and the second radially outer annular cavity being downstream from the disk, the radially inner annular cavity having a first portion extending upstream of said at least one bladed rotor disk and a second portion extending downstream of said at least one bladed rotor disk;
- and
- fluid injectors for providing from a combustion chamber end, where air temperature is lower than that of combustion gas issued from said combustion chamber, a stream of air to the first radially outer annular cavity,
- wherein the upstream flange of the disk includes means for passing said stream of air from the first radially outer annular cavity to the first portion of the radially inner annular cavity, and the downstream flange of the disk includes means for passing said stream of air from the second portion of the radially inner annular cavity to the second radially outer annular cavity,
- wherein the radially inner annular cavity is delimited radially inwards by a cylindrical shroud or sheath having an upstream end fastened to a first component carrying the upstream flange of the disk, and having a downstream end fastened to a second component carrying the downstream flange of the disk, so that said stream of air passes from the first portion to the second portion of the radially inner annular cavity.
2 more elements
Dependencies are inferred from the claim text.