REVERSED-FLOW CORE FOR A TURBOFAN WITH A FAN DRIVE GEAR SYSTEM

• US 20110056208A1
• Filed: 09/09/2009
• Published: 03/10/2011
• Est. Priority Date: 09/09/2009
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Norris, James W., Berryann, Andrew P., Costa, Mark W., Epstein, Alan, Kupratis, Daniel B., Roberge, Gary D.
• Granted Patent: US 8,176,725 B2
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02K 3/105 Heating the by-pass flow
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

1. A gas turbine engine comprising:

a fan drive gear system;

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 low pressure compressor; and

a high spool disposed aft of the low spool, the high spool comprising;

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.

2. The gas turbine engine of claim 1 wherein flow through the engine extends sequentially through the low pressure compressor in a downstream direction, and through the high pressure compressor, the combustor, the high pressure turbine and the low pressure turbine in a forward direction.

3. The gas turbine engine of claim 2 wherein the fan drive gear system comprises:

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.

4. The gas turbine engine of claim 3 and further comprising:

a low pressure shaft comprising;

a forward portion connected to the epicyclic gear system;

a mid portion connected to the low pressure compressor; and

an aft portion connected to the low pressure turbine; and

a high pressure shaft disposed axially downstream of the low pressure shaft, the high pressure shaft comprising;

a forward portion connected to the high pressure turbine;

a mid portion extending concentrically through the combustor; and

an aft portion connected to the high pressure compressor.

5. The gas turbine engine of claim 4 and further comprising an accessory gearbox extending axially from a downstream end of the high pressure shaft.

6. The gas turbine engine of claim 5 and further comprising an accessory gearbox extending radially from the low pressure shaft using a tower shaft.

7. The gas turbine engine of claim 4 and further comprising a balance piston and a tapered roller bearing connected to the low pressure shaft to react axially forward directed thrust on the low pressure spool.

8. The gas turbine engine of claim 3 and further comprising:

an intermediate pressure turbine disposed between the low pressure turbine and the high pressure turbine;

a gear shaft connecting the epicyclic gear system to the intermediate pressure turbine;

a low pressure shaft comprising;

a forward portion connected to the low pressure compressor; and

an aft portion connected to the low pressure turbine; and

a high pressure shaft disposed axially downstream of the low pressure shaft, the high pressure shaft comprising;

a forward portion connected to the high pressure turbine;

a mid portion extending concentrically through the combustor; and

an aft portion connected to the high pressure compressor.

9. The gas turbine engine of claim 3 and further comprising:

reverse ducting disposed radially outward of the high spool for directing output of the low pressure compressor to the high pressure compressor such that the output reverses flow to pass through the high spool; and

exhaust ducting disposed radially outward of the reverse ducting for receiving exhaust gas from the low pressure turbine and fan air from the turbofan.

10. The turbine engine of claim 9 and further comprising an intercooling and recuperating heat exchanger mounted adjacent the reverse ducting between the low pressure compressor and the high pressure compressor.

11. The gas turbine engine of claim 9 and further comprising an augmenter mounted within the exhaust ducting radially outward of the high pressure spool.

12. The gas turbine engine of claim 3 and further comprising:

an annular exhaust duct for guiding fan air from the turbofan;

a flow splitter disposed within the exhaust duct to divert a portion of the fan air to the low pressure compressor to produce a downstream flow of low pressure air;

a core engine case surrounding the high spool;

a reverse flow duct disposed concentrically between the exhaust duct and the core engine case, the reverse flow duct comprising;

an inlet end configured to receive downstream flow of the low pressure air from the low pressure compressor;

an elbow connected to the inlet end and configured to redirect downstream flow of the low pressure air into upstream flow; and

an outlet end connected to the elbow and configured to direct upstream flow of the low pressure air into the high pressure compressor; and

an exhaust vent comprising;

an inlet configured to receive gas from the core engine case; and

an outlet configured to discharge gas into the annular exhaust duct.

13. The gas turbine engine of claim 3 wherein the high pressure compressor comprises an axial flow compressor.

14. A turbofan engine comprising:

a turbofan propulsor for producing downstream flowing bypass gas and core gas;

a cross-flow 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;

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; and

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.

15. The turbofan engine of claim 14 wherein the reversed-flow core includes an axial flow high pressure turbine and an axial flow high pressure compressor.

16. The turbofan engine of claim 15 and further comprising:

a fan shaft for connecting the turbofan propulsor to the gear reduction system;

a low pressure shaft for connecting the low pressure compressor to the low pressure turbine; and

a high pressure shaft for connecting the high pressure compressor to the high pressure turbine.

17. The turbofan engine of claim 16 and further comprising a gear shaft for connecting the gear reduction system to the cross-flow low pressure spool, the gear shaft providing the input rotation.

18. The turbofan engine of claim 16 and further comprising:

an intermediate pressure turbine disposed between the low pressure turbine and the high pressure turbine; and

a gear shaft for connecting the gear reduction system to the intermediate pressure turbine, the gear shaft providing the input rotation.

19. A method for operating a turbofan engine, the method comprising:

generating an axially downstream flow of fan air with a fan drive gear system;

splitting the fan air into a first portion directed downstream into an exhaust duct, and a second portion directed downstream into a low pressure compressor;

redirecting compressed air from the low pressure compressor to a reverse flow duct to produce an axially upstream flow of compressed air;

directing the upstream flow of compressed air sequentially through a high pressure compressor, a combustor, a high pressure turbine and a low pressure turbine to produce exhaust gas; and

venting the exhaust gas into the exhaust duct to join the first portion of the fan air.

20. The method of claim 19 wherein the reverse flow duct is radially inward and concentric with the exhaust duct;

and the high pressure compressor, the combustor, the high pressure turbine and the low pressure turbine are radially inward and concentric with the reverse flow duct such that the exhaust gas is vented radially outward to the exhaust duct through the reverse flow duct.