초록 ▼

The invention relates to a method of supplying cooling air to the hot portions of a turbojet that comprises, from upstream to downstream: a compressor; a diffuser; a combustion chamber; a distributor; and a turbine driving said compressor, in which method a flow of air is bled from the flow of air d

The invention relates to a method of supplying cooling air to the hot portions of a turbojet that comprises, from upstream to downstream: a compressor; a diffuser; a combustion chamber; a distributor; and a turbine driving said compressor, in which method a flow of air is bled from the flow of air delivered by the compressor, the bled-off flow is cooled in a heat exchanger situated radially outside the combustion chamber, and is then directed radially inwards via the stationary blades of the distributor and used for cooling the moving wheel of the turbine, the method wherein the flow of cooling air is bled from the zone of the end of the combustion chamber that surrounds the diffuser, and wherein the stationary blades of the distributor are also cooled by a second flow of air bled from the diffuser.

대표청구항 ▼

What is claimed is: 1. A method of delivering cooling air to the hot portions of a turbojet that comprises, from upstream to downstream: a compressor; a diffuser; a combustion chamber; a distributor; and a turbine driving said compressor, in which method, a flow of air is bled from the flow of air

What is claimed is: 1. A method of delivering cooling air to the hot portions of a turbojet that comprises, from upstream to downstream: a compressor; a diffuser; a combustion chamber; a distributor; and a turbine driving said compressor, in which method, a flow of air is bled from the flow of air delivered by the compressor, which bled-off flow is cooled in a heat exchanger situated radially outside the combustion chamber, and is then directed radially inwards via stationary blades of the distributor and used to cool the moving wheel of the turbine, the method wherein the cooling air flow is bled from the zone at the upstream end of the combustion chamber surrounding the diffuser, and wherein the stationary blades of the distributor are cooled by a second air flow bled from the downstream of said diffuser. 2. A method according to claim 1, wherein a fraction of the flow of air passing through the distributor is channeled beneath the combustion chamber towards the last stage of the compressor in order to cool the cavity thereof. 3. A turbojet comprising, from upstream to downstream: a compressor; a diffuser; a combustion chamber; a distributor; and a turbine driving said compressor; the turbojet further comprising a first cooling circuit having means for bleeding air from the flow delivered by the compressor, a heat exchanger situated radially outside the combustion chamber, and means for directing the cooled air through the stationary blades of the distributor in order to cool the moving wheel of the turbine, wherein the bleed means bleed the flow of air from the zone of the end of the combustion chamber that surrounds the diffuser, and further comprising a second circuit for cooling the stationary blades of the distributor which bleeds air from the diffuser. 4. A turbojet according to claim 3, further comprising a channel beneath the combustion chamber to bring a fraction of the flow of air passing through the distributor towards the last stage of the compressor.