Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.

Abstract: A system and method are disclosed for providing geocoded web content to a user based on a specific geographic location specified by the user. A determination module receives a geographic location from the user and determines latitude and longitude coordinates associated with the geographic location from a geographic information database. The determination module further determines a geographic boundary associated with the latitude and longitude coordinates based at least in part on an area of interest surrounding the geographic location. A web content search module determines web content comprising substance associated with a location within the geographic boundary. A front end interface transmits the determined web content for display in an order based at least in part on distance from the location associated with the web content to the geographic location.

Abstract: In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.

Abstract: A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.

Abstract: In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.

Abstract: A gas turbine engine according to an exemplary aspect of the present invention includes a gear train defined along an engine centerline axis, and a spool along the engine centerline axis which drives the gear train, the spool includes a low stage count low pressure turbine.

Abstract: In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four (4) stages.

Abstract: A gas turbine engine according to an exemplary aspect of the present invention includes a gear train defined along an engine centerline axis, and a spool along the engine centerline axis which drives the gear train, the spool includes a low stage count low pressure turbine.

Abstract: A mount system for a gas turbine engine includes an aft mount which reacts at least a portion of a thrust load at an engine case generally parallel to an engine axis.

Abstract: In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.

Abstract: A system and method are disclosed for providing geocoded web content to a user based on a specific geographic location specified by the user. A determination module receives a geographic location from the user and determines latitude and longitude coordinates associated with the geographic location from a geographic information database. The determination module further determines a geographic boundary associated with the latitude and longitude coordinates based at least in part on an area of interest surrounding the geographic location. A web content search module determines web content comprising substance associated with a location within the geographic boundary. A front end interface transmits the determined web content for display in an order based at least in part on distance from the location associated with the web content to the geographic location.

Abstract: A mount system for a gas turbine engine includes an aft mount which reacts at least a portion of a thrust load at an engine case generally parallel to an engine axis.