GAS TURBINE ENGINE ARCHITECTURE WITH SPLIT COMPRESSOR SYSTEM

• US 20180216525A1
• Filed: 01/30/2017
• Published: 08/02/2018
• Est. Priority Date: 01/30/2017
• Status: Abandoned Application

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: PLANTE, Ghislain, VALOIS, Patrick, DUBREUIL, Jean, BLAIS, Daniel
• Application Number:
  US15/419,160
• Publication Number:
  US 20180216525A1
• Time in Patent Office: Days
• CPC Class Codes: B64D 27/10 of gas-turbine type jet aircraft B64D27/16
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• 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: F05D 2220/325 to drive unshrouded, high solidity propeller
• CPC Class Codes: F05D 2250/312 the axes being parallel to each other
• CPC Class Codes: F05D 2260/4031 as in toothed gearing
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine has an engine core including a low pressure compressor, a high pressure compressor, a high pressure turbine and a low pressure turbine coaxially mounted about an engine axis and fluidly connected in series by a core gaspath. The low pressure turbine is drivingly connected to the low pressure compressor via an external shaft disposed radially outwardly of the core gaspath.

Claims

1. A gas turbine engine comprising:

an engine core including a low pressure compressor, a high pressure compressor, a high pressure turbine and a low pressure turbine fluidly connected in series by an annular core gaspath concentric to an engine axis; and

an external shaft disposed radially outwardly of an outer circumference of the core gaspath and drivingly connecting the low pressure turbine to the low pressure compressor.

2. The gas turbine engine defined in claim 1, wherein the high pressure turbine is drivingly connected to the high pressure compressor via a high pressure shaft, the high pressure shaft being spaced radially inwardly from the core gaspath.

3. The gas turbine engine defined in claim 2, wherein the high pressure shaft is coaxial to the engine axis, and wherein the external shaft connecting the low pressure turbine to the low pressure compressor is radially offset from the high pressure shaft.

4. The gas turbine engine defined in claim 3, wherein the external shaft is parallel to the high pressure shaft.

5. The gas turbine engine defined in claim 1, wherein a geared connection is provided between the external shaft and at least one of the low pressure compressor and the low pressure turbine to allow the low pressure compressor to be driven at a different speed from that of the low pressure turbine.

6. The gas turbine engine defined in claim 1, wherein a gear set is operatively connected to the external shaft and configured for inverting a rotational direction of the low pressure compressor relative to the low pressure turbine.

7. The gas turbine engine defined in claim 1, wherein the external shaft is operatively connected to a mechanical link configured to cause a rotational direction of the low pressure compressor to be opposite to that of the low pressure turbine.

8. The gas turbine engine defined in claim 1, wherein the external shaft has an input end connected to a downstream side of the low pressure turbine relative to a flow of gas through the core gaspath.

9. The gas turbine engine defined in claim 1, wherein the external shaft has an output end connected to an upstream side of the low pressure compressor relative to a flow of gas through the core gaspath.

10. The gas turbine engine defined in claim 9, wherein the low pressure compressor is located at a rear end portion of the engine whereas the low pressure turbine is located at a front end portion of the engine, a gas flowing through the core gaspath from the rear end portion to the front end portion of the engine.

11. The gas turbine engine defined in claim 1, wherein the external shaft has an input end connected to an upstream side of the low pressure turbine and an output end connected to a downstream side of the low pressure compressor relative to a flow of gas through the core gaspath.

12. The gas turbine engine defined in claim 1, further comprising an accessory gearbox (AGB), and wherein the low pressure turbine is drivingly connected to the AGB via the external shaft.

13. The gas turbine engine defined in claim 12, wherein the high pressure turbine is also drivingly connected to the AGB, the AGB having first and second power inputs respectively provided by the low and high pressure turbines.

14. The gas turbine engine defined in claim 1, wherein the external shaft extends axially from a location upstream of the high pressure compressor to a location downstream of the high pressure turbine.

15. The gas turbine engine defined in claim 1, wherein the high pressure turbine is drivingly connected to the high pressure compressor by a high pressure shaft coaxial to the engine axis;

the high pressure turbine, the high pressure shaft and the high pressure compressor form a high pressure spool, and wherein the external shaft axially spans the high pressure spool.

16. The gas turbine engine defined in claim 1, wherein the low pressure turbine comprises a low pressure shaft drivingly connected to a reduction gearbox (RGB) or to a load external to the engine.

17. The gas turbine engine defined in claim 16, further comprising a propeller drivingly connected to an output end of the RGB.

18. A gas turbine engine comprising:

an engine core including a low pressure compressor, a high pressure compressor, a high pressure turbine and a low pressure turbine coaxially mounted along an engine centerline and fluidly connected in series by a core gaspath; and

a low pressure shaft disposed outside of the engine core and drivingly connecting the low pressure turbine to the low pressure compressor.

19. The gas turbine engine defined in claim 18, wherein the low pressure shaft axially spans the high pressure turbine and the high pressure compressor.

20. The gas turbine engine defined in claim 19, wherein the low pressure shaft is spaced radially outwardly from the core gaspath.