Reversed-flow core for a turbofan with a fan drive gear system
First Claim
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1. A gas turbine engine comprising:
- a fan drive gear system comprising;
a turbofan;
a fan shaft connected to an inner diameter of the turbofan; and
an epicyclic gear system connected to a downstream end of the fan shaft;
a low spool connected to the fan drive gear system, the low spool comprising;
a rearward-flow low pressure compressor disposed aft of the fan drive gear system; and
a forward-flow low pressure turbine disposed aft of the rearward-flow low pressure compressor;
a high spool disposed aft of the low spool, the high spool comprising;
a forward-flow high pressure turbine disposed aft of the forward-flow low pressure turbine;
a combustor disposed aft of the forward-flow high pressure turbine; and
a forward-flow high pressure compressor disposed aft of the combustor;
a reverse ducting disposed radially outward of the high spool for directing output of the rearward-flow low pressure compressor to the forward-flow high pressure compressor such that the output reverses flow to pass through the high spool;
exhaust ducting disposed radially outward of the reverse ducting for receiving exhaust gas from the forward-flow low pressure turbine and fan air from the turbofan; and
an intercooling and recuperating heat exchanger mounted adjacent the reverse ducting between the rearward-flow low pressure compressor and the forward-flow high pressure compressor;
wherein flow through the engine extends sequentially through the rearward-flow low pressure compressor in a downstream direction, and through the forward-flow high pressure compressor, the combustor, the forward-flow high pressure turbine and the forward-flow low pressure turbine in a forward direction.
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Abstract
A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor.
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Citations
20 Claims
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1. A gas turbine engine comprising:
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a fan drive gear system comprising; a turbofan; a fan shaft connected to an inner diameter of the turbofan; and an epicyclic gear system connected to a downstream end of the fan shaft; a low spool connected to the fan drive gear system, the low spool comprising; a rearward-flow low pressure compressor disposed aft of the fan drive gear system; and a forward-flow low pressure turbine disposed aft of the rearward-flow low pressure compressor; a high spool disposed aft of the low spool, the high spool comprising; a forward-flow high pressure turbine disposed aft of the forward-flow low pressure turbine; a combustor disposed aft of the forward-flow high pressure turbine; and a forward-flow high pressure compressor disposed aft of the combustor; a reverse ducting disposed radially outward of the high spool for directing output of the rearward-flow low pressure compressor to the forward-flow high pressure compressor such that the output reverses flow to pass through the high spool; exhaust ducting disposed radially outward of the reverse ducting for receiving exhaust gas from the forward-flow low pressure turbine and fan air from the turbofan; and an intercooling and recuperating heat exchanger mounted adjacent the reverse ducting between the rearward-flow low pressure compressor and the forward-flow high pressure compressor; wherein flow through the engine extends sequentially through the rearward-flow low pressure compressor in a downstream direction, and through the forward-flow high pressure compressor, the combustor, the forward-flow high pressure turbine and the forward-flow low pressure turbine in a forward direction. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A turbofan engine comprising:
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a turbofan propulsor for producing downstream flowing bypass gas and core gas; a low pressure spool comprising; a low pressure compressor for receiving downstream flowing core gas from the turbofan propulsor; and a low pressure turbine having upstream flow; a gear reduction system for coupling the turbofan propulsor to an input rotation; a reverse air duct for turning downstream flowing core gas from the low pressure compressor radially inward for upstream flow; a reversed-flow core with upstream flow configured to receive upstream flowing core gas from the air duct and to deliver upstream flowing core gas to the low pressure turbine; an exhaust pipe for turning upstream flow of core gas from the low pressure turbine radially outward for discharge into the downstream flow of bypass gas; and an intercooling and recuperating heat exchanger mounted adjacent the reverse air duct between the low pressure compressor and the reversed-flow core. - View Dependent Claims (10, 11, 12, 13)
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14. A gas turbine engine comprising:
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a fan drive gear system comprising; a turbofan; a fan shaft connected to an inner diameter of the turbofan; and an epicyclic gear system connected to a downstream end of the fan shaft; a low spool connected to the fan drive gear system, the low spool comprising; a low pressure shaft; a rearward-flow low pressure compressor disposed aft of the fan drive gear system; and a forward-flow low pressure turbine disposed aft of the rearward-flow low pressure compressor; a high spool disposed aft of the low spool, the high spool comprising; a forward-flow high pressure turbine disposed aft of the forward-flow low pressure turbine; a combustor disposed aft of the forward-flow high pressure turbine; and a forward-flow high pressure compressor disposed aft of the combustor; reverse ducting disposed radially outward of the high spool for directing output of the rearward-flow low pressure compressor to the forward-flow high pressure compressor such that the output reverses flow to pass through the high spool; exhaust ducting disposed radially outward of the reverse ducting for receiving exhaust gas from the forward-flow low pressure turbine and fan air from the turbofan; and an augmenter mounted within the exhaust ducting radially outward of the high pressure spool; wherein flow through the engine extends sequentially through the rearward-flow low pressure compressor in a downstream direction, and through the forward-flow high pressure compressor, the combustor, the forward-flow high pressure turbine and the forward-flow low pressure turbine in a forward direction; and wherein an accessory gearbox extending radially from the low pressure shaft using a tower shaft. - View Dependent Claims (15, 16, 17, 18, 19)
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20. A turbofan engine comprising:
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a turbofan propulsor for producing downstream flowing bypass gas and core gas; a low pressure spool comprising; a low pressure shaft; a low pressure compressor for receiving downstream flowing core gas from the turbofan propulsor; and a low pressure turbine having upstream flow; a gear reduction system for coupling the turbofan propulsor to an input rotation; an air duct for turning downstream flowing core gas from the low pressure compressor radially inward for upstream flow; a reversed-flow core with upstream flow configured to receive upstream flowing core gas from the air duct and to deliver upstream flowing core gas to the low pressure turbine; an exhaust pipe for turning upstream flow of core gas from the low pressure turbine radially outward for discharge into the downstream flow of bypass gas; and
an augmenter mounted within an exhaust ductradially outward of the reversed-flow core; wherein an accessory gearbox extending radially from the low pressure shaft using a tower shaft.
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Specification