Gas turbine engine
A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. The core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction. The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.
1 . A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
a turbomachine having an unducted primary fan, a core engine including a combustor and a combustor casing enclosing the combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine and defining an inner surface and an outer surface, the core engine including a compressor section upstream of the combustor;
wherein the outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction, the core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction,
wherein the gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L),
wherein the CDR is between 2.7 and 3.5 and wherein the CLR is between 0.25 and 0.50, and
an air management system in the core cowl, the air management system including conduits to extract pressurized air from one or more stages of the compressor section.
2 . The gas turbine engine of claim 1 , wherein the air management system includes:
a jet pump including a throat, a plurality of suction inlets, and an outlet;
a first conduit to direct a portion of relatively high pressure air extracted from the compressor section through a jet pump shutoff valve (JPSOV) to the throat of the jet pump;
a second conduit to direct a portion of the relatively high pressure air through a high-pressure shutoff valve (HPSOV) to at least one of the plurality of suction inlets of the jet pump; and
a third conduit configured to direct relatively low pressure air extracted from the compressor section to at least one of the plurality of suction inlets of the jet pump.
3 . The gas turbine engine of claim 2 , wherein the air management system is configured to operate in:
a first mode in which the JPSOV and the HPSOV are in a closed position;
a second mode in which the JPSOV is in a closed position and the HPSOV is in an open position; and
a third mode in which the JPSOV is in an open position and the HPSOV is in a closed position.
4 . The gas turbine engine of claim 2 , wherein the air management system includes a pressure sensor coupled to the first conduit between the JPSOV and the throat.
5 . The gas turbine engine of claim 4 , further including a controller to control the JPSOV based on a pressure signal from the pressure sensor.
6 . The gas turbine engine of claim 2 , wherein the relatively high pressure air is from a higher stage of a high pressure compressor, and the relatively low pressure air is from a lower stage of the high pressure compressor.
7 . The gas turbine engine of claim 1 , further including a ventilation system to vent a sump, the sump containing a bearing that supports a shaft of the gas turbine engine.
8 . The gas turbine engine of claim 7 , wherein the ventilation system includes an eductor in the core cowl.
9 . The gas turbine engine of claim 8 , wherein the air management system is fluidly coupled to the eductor to provide a motive force to suction fluid from the sump.
10 . The gas turbine engine of claim 9 , wherein the eductor includes a suction port, an outlet port, a motive inlet port, and a nozzle.
11 . An aircraft, comprising:
a wing; and
a gas turbine engine mounted to the wing, the gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
a turbomachine having an unducted primary fan, a core engine including a combustor and a combustor casing enclosing the combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine and defining an inner surface and an outer surface, the core engine including a compressor section upstream of the combustor;
wherein the outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction, the core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction,
wherein the gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L),
wherein the CDR is between 2.7 and 3.5 and wherein the CLR is between 0.25 and 0.50, and
an air management system in the core cowl, the air management system including conduits to extract pressurized air from one or more stages of the compressor section.
12 . The aircraft of claim 11 , wherein the air management system includes:
a jet pump including a throat, a plurality of suction inlets, and an outlet;
a first conduit to direct a portion of relatively high pressure air extracted from the compressor section through a jet pump shutoff valve (JPSOV) to the throat of the jet pump;
a second conduit to direct a portion of the relatively high pressure air through a high-pressure shutoff valve (HPSOV) to at least one of the plurality of suction inlets of the jet pump; and
a third conduit configured to direct relatively low pressure air extracted from the compressor section to at least one of the plurality of suction inlets of the jet pump.
13 . The aircraft of claim 12 , wherein the air management system is configured to operate in:
a first mode in which the JPSOV and the HPSOV are in a closed position;
a second mode in which the JPSOV is in a closed position and the HPSOV is in an open position; and
a third mode in which the JPSOV is in an open position and the HPSOV is in a closed position.
14 . The aircraft of claim 12 , wherein the air management system includes a pressure sensor coupled to the first conduit between the JPSOV and the throat.
15 . The aircraft of claim 14 , further including a controller to control the JPSOV based on a pressure signal from the pressure sensor.
16 . The aircraft of claim 12 , wherein the relatively high pressure air is from a higher stage of a high pressure compressor, and the relatively low pressure air is from a lower stage of the high pressure compressor.
17 . The aircraft of claim 11 , further including a ventilation system to vent a sump, the sump containing a bearing that supports a shaft of the gas turbine engine.
18 . The aircraft of claim 17 , wherein the ventilation system includes an eductor in the core cowl.
19 . The aircraft of claim 18 , wherein the air management system is fluidly coupled to the eductor to provide a motive force to suction fluid from the sump.
20 . The aircraft of claim 19 , wherein the eductor includes a suction port, an outlet port, a motive inlet port, and a nozzle.