Compressor bleed air exhaust ducting for gas turbine engine systems
A gas turbine engine system includes an enclosure, a compressor assembly located at least partially within the enclosure, and a bleed-duct joint. The compressor assembly includes a compressor and a bleed-air collector having a bleed-air manifold configured to receive a portion of air compressed by the compressor and a bleed-air duct extending through an aperture in the enclosure to direct the portion of the air outside of the enclosure. The bleed-air duct includes a first pipe coupled to the compressor for movement with the compressor and a second pipe extending through the aperture in the first wall and arranged around the first pipe. The bleed-duct joint is configured to couple the bleed-air duct with the enclosure to locate the second pipe relative to the first pipe.
1 . A gas turbine engine system comprising:
an enclosure having a plurality of walls that cooperate to define a cavity within the enclosure, the plurality of walls including a first wall formed to define an aperture therethrough,
a compressor assembly configured to collect compressor bleed air, the compressor assembly including a compressor located within the cavity and configured to compress air received from within the enclosure and a bleed-air collector having a bleed-air manifold configured to receive a portion of the air compressed by the compressor and a bleed-air duct extending through the aperture in the first wall to direct the portion of the air through the aperture formed in the first wall of the enclosure, the bleed-air duct having a first pipe coupled to the compressor for movement with the compressor and a second pipe extending through the aperture in the first wall and arranged around the first pipe, and
a bleed-duct joint configured to couple the bleed-air duct with the enclosure, the bleed-duct joint coupled with the second pipe and the first wall of the enclosure to locate the second pipe relative to the first pipe so that the first pipe is spaced apart from the second pipe to mechanically decouple the first pipe from the second pipe and allow for thermal growth of the first pipe during operation of the gas turbine engine system.
2 . The gas turbine engine system of claim 1 , wherein the bleed-duct joint includes an attachment bracket coupled with the second pipe for movement with the second pipe, the attachment bracket is coupled with the first wall to locate the second pipe relative to the enclosure.
3 . The gas turbine engine system of claim 2 , wherein the attachment bracket is formed to define a longitudinally extending slot.
4 . The gas turbine engine system of claim 3 , wherein the first wall is formed to define a slot perpendicular to the longitudinally extending slot.
5 . The gas turbine engine system of claim 4 , wherein a fastener couples the attachment bracket to the first wall, the fastener extending between the slot in the first wall and the longitudinally extending slot in the attachment bracket.
6 . The gas turbine engine system of claim 5 , wherein the fastener is arranged to slide within the slot in the first wall and the longitudinally extending slot in the attachment bracket to locate the second pipe.
7 . The gas turbine engine system of claim 2 , wherein the first wall is formed to define a slot adjacent to the aperture, a fastener coupling the attachment bracket to the first wall arranged to extend through and slide within the slot to locate the second pipe.
8 . The gas turbine engine system of claim 2 , wherein the bleed-duct joint includes a seal assembly configured to block fluid from entering the compressor through the aperture.
9 . The gas turbine engine system of claim 8 , wherein the seal assembly includes a rain shield coupled to the second pipe and extending past an outer circumference of the aperture.
10 . The gas turbine engine system of claim 9 , wherein the seal assembly further includes a seal located between the first wall and the rain shield, the rain shield arranged to contact the seal to block fluid from entering the bleed-duct joint from between the first wall and the rain shield.
11 . The gas turbine engine system of claim 10 , wherein the seal assembly further includes a spacer coupled with the first wall and arranged around the aperture and the second pipe to form a closed perimeter of the bleed-duct joint.
12 . The gas turbine engine system of claim 11 , wherein the seal is coupled to the spacer and the rain shield is arranged to rest on top of the seal and the spacer to allow the rain shield to move relative to the first wall.
13 . The gas turbine engine system of claim 9 , wherein the second pipe includes an outer portion disposed outside of the enclosure and an inner portion coupled to the outer portion and arranged to extend through the aperture towards the compressor.
14 . The gas turbine engine system of claim 13 , wherein the rain shield is disposed between the inner portion and the outer portion to couple the rain shield to the second pipe and create a seal.
15 . A gas turbine engine system comprising:
an enclosure having a plurality of walls that cooperate to define a cavity within the enclosure, the plurality of walls including a first wall formed to define an aperture therethrough,
a compressor assembly configured to collect compressor bleed air, the compressor assembly including a compressor located within the cavity and configured to compress air received from within the enclosure and a bleed-air collector configured to receive a portion of the air compressed by the compressor and including a bleed-air duct extending through the aperture in the first wall to direct the portion of the air through the aperture formed in the first wall of the enclosure, the bleed-air duct having a first pipe coupled to the compressor and a second pipe extending through the aperture in the first wall and arranged around the first pipe, and
a bleed-duct joint configured to couple the bleed-air duct with the enclosure, the bleed-duct joint coupled with the second pipe and the first wall of the enclosure to locate the second pipe relative to the first pipe so that the first pipe is spaced apart from the second pipe to mechanically decouple the first pipe from the second pipe.
16 . The gas turbine engine system of claim 15 , wherein the bleed-duct joint includes an attachment bracket coupled with the second pipe for movement with the second pipe, the attachment bracket is coupled with the first wall to locate the second pipe relative to the enclosure.
17 . The gas turbine engine system of claim 16 , wherein the attachment bracket is formed to define a longitudinally extending slot.
18 . The gas turbine engine system of claim 17 , wherein the first wall is formed to define a slot perpendicular to the longitudinally extending slot.
19 . The gas turbine engine system of claim 18 , wherein a fastener couples the attachment bracket to the first wall, the fastener extending between the slot in the first wall and the longitudinally extending slot in the attachment bracket.