GAS TURBINE ENGINE

• US 20170370284A1
• Filed: 05/23/2017
• Published: 12/28/2017
• Est. Priority Date: 06/22/2016
• Status: Abandoned Application

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: HARVEY, Giles E., KNIGHT, Glenn A.
• Application Number:
  US15/602,429
• Publication Number:
  US 20170370284A1
• Time in Patent Office: Days
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02C 7/143 before or between the compressor stages
• 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 3/06 with front fan
• CPC Class Codes: F05D 2260/213 by the provision of a heat exchanger within the cooling circuit
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine (10) comprises:

• a low pressure compressor (18) comprising a centrifugal compressor stage (24);
• a low pressure turbine (44) configured to drive a load (12), the low pressure turbine (44) being provided rearwardly of the low pressure compressor (18);
• a high pressure turbine (42) provided rearwardly of the low pressure turbine (44);
• a combustor (40) provided rearwardly of the high pressure turbine (42);
• a high pressure compressor (32) provided rearwardly of the combustor (40); and
• an intercooler heat exchanger (28) configured to exchange heat between core airflow (B) exiting the low pressure compressor (18) and fan airflow (A), wherein the high pressure turbine (42) and high pressure compressor (32) are coupled by a high pressure shaft (46), and the low pressure turbine (44), low pressure compressor (18) and load (12) are coupled by a low pressure shaft (22).

Claims

1. A gas turbine engine comprising:

a low pressure module comprising a low pressure compressor comprising

a centrifugal compressor stage, and a low pressure turbine configured to drive a load

a high pressure module comprising a high pressure turbine, a combustor and a high pressure compressor, the high pressure module being provided axially spaced from the low pressure module; and

an intercooler heat exchanger configured to exchange heat between core airflow exiting the low pressure compressor and ambient airflow, wherein the high pressure turbine and high pressure compressor are coupled by a high pressure shaft, and the low pressure turbine, low pressure compressor and load are coupled by a low pressure coupling.

2. A gas turbine engine according to claim 1, wherein the load driven by the low pressure turbine comprises a fan configured to provide a fan outlet flow in a rearward direction.

3. A gas turbine engine according to claim 2, wherein the fan is provided forwardly of the low pressure turbine.

4. A gas turbine engine according to claim 1, wherein the high pressure compressor is configured to transfer flow in a forward direction generally opposite to the rearward direction.

5. A gas turbine engine according to claim 1, wherein the combustor is configured to receive core flow from the high pressure compressor, and deliver flow from a compressor outlet in the forward direction.

6. A gas turbine engine according to claim 1, wherein the high pressure turbine is configured to receive flow from the combustor and deliver flow from to the low pressure turbine.

7. A gas turbine engine according to claim 1, wherein the low pressure turbine load is coupled to the low pressure turbine by a reduction gearbox.

8. A gas turbine engine according to claim 7, wherein the reduction gearbox is provided between the low pressure compressor and the load.

9. A gas turbine engine according to claim 1, wherein the low pressure turbine is provided between the combustor and the low pressure compressor.

10. A gas turbine engine according to claim 1, wherein the high pressure compressor comprises one or both of at least one axial flow compressor stage and at least one centrifugal flow compressor stage.

11. A gas turbine according to claim 1, wherein the low pressure compressor further comprises an axial flow compressor upstream of the centrifugal flow compressor, and coupled to the low pressure shaft.

12. A gas turbine engine according to claim 1, wherein the intercooler heat exchanger comprises an interstage duct extending between a low pressure compressor outlet and a high pressure compressor inlet.

13. A gas turbine engine according to claim 12, wherein the interstage duct is provided radially outwardly of the high pressure compressor and high pressure turbine.

14. A gas turbine engine according to claim 13, wherein the engine comprises a core exhaust duct configured to redirect core exhaust from a low pressure turbine outlet in the first rearward direction, wherein the interstage duct and core exhaust duct may extend generally parallel to one another.

15. A gas turbine engine according to claim 14, wherein a plurality of core exhaust ducts and interstage ducts are arranged alternately with one another, and are circumferentially spaced around the engine.

16. A gas turbine engine according to claim 1, wherein the engine comprises a bypass ratio of 10 or greater.