TWO SPOOL ENGINE CORE WITH A STARTER

• US 20150330300A1
• Filed: 12/30/2013
• Published: 11/19/2015
• Est. Priority Date: 03/14/2013
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Suciu, Gabriel L., Merry, Brian D.
• Application Number:
  US14/142,965
• Publication Number:
  US 20150330300A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F02C 3/10 with another turbine driving an output shaft but not driving the compressor
• CPC Class Codes: F02C 7/27 Fluid drives turbine starters F02C7/277
• CPC Class Codes: F02C 7/275 Mechanical drives
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other

Abstract

A gas turbine engine has a first spool, a second spool, and a one-way clutch connecting the first and second spools. The one-way clutch disengages from the second spool when the first and second spools rotate at a predetermined speed.

Claims

1. An engine comprising:

a first spool and a second spool; and

a one-way clutch connecting said first and second spools, said one-way clutch disengaging from said second spool when the second spool and the first spool rotate at a predetermined speed.

2. The engine according to claim 1, wherein the first spool is a low spool and the second spool is the high spool and wherein the predetermined speed is a speed at which the high spool rotates faster than the low spool.

3. The engine according to claim 1, wherein a combustor burns fuel at the predetermined speed.

4. The engine of claim 2, further comprising a starter connected to a tip of said low spool and said starter providing initial torque to said high and low spools, whereby said high and low spools rotate substantially from rest to said predetermined speed at the same speed.

5. The engine according to claim 4, wherein said starter is located at an axial tip of said low spool.

6. The engine of claim 4, wherein said engine has a low pressure compressor having a rotor and said starter is mounted to said rotor of said low pressure compressor.

7. The engine of claim 4, wherein said starter is an electrical starter.

8. The engine of claim 4, wherein said starter is a pneumatic starter.

9. The engine of claim 4, further comprising an oil pump, a fuel pump, said starter acting as a generator, and a shaft connected to low pressure compressor gear located in between the starter acting as the generator and an inlet to a low pressure compressor to extract shaft horsepower to run said oil and fuel pumps.

10. The engine of claim 4, wherein said starter functions as a generator for powering electrical components.

11. The engine of claim 4, wherein excess power from said starter is delivered to an airframe to operate electronics.

12. The engine of claim 4, wherein said engine is a reverse engine core.

13. The engine of claim 1, further comprising a low pressure compressor and a high pressure compressor and said low pressure compressor being larger in size than said high pressure compressor.

14. The engine of claim 13, wherein the ratio of low pressure compressor pressure ratio to high pressure compressor pressure ratio is in a range of from greater than 2:

1 to 4;

1.

15. A propulsion system comprising:

a propulsor comprising a free turbine and a fan driven by said free turbine;

a two spool engine for providing exhaust fluid for driving said free turbine;

said two spool engine having a first spool and a second spool; and

a one-way clutch connecting said first and second spools, said one-way clutch disengaging from said second spool when said second spool and said first spool rotate at a predetermined speed.

16. The propulsion system of claim 15, wherein said first spool is a low spool, said second spool is a high spool, and said second spool rotates at a speed faster than said first spool.

17. The propulsion system of claim 15, wherein said engine has a combustor burning fuel at the predetermined speed.

18. The propulsion system of claim 16, further comprising said engine having a low pressure compressor and a low pressure turbine connected by said low spool, a high pressure compressor and a high pressure turbine connected by said high spool, a combustor positioned between said high pressure compressor and said high pressure turbine, and said one-way clutch disengaging from said high spool when said combustor lights and fuel burns and said high spool rotates faster than said low spool so that said high spool rotates freely.

19. The propulsion system according to claim 15, further comprising a diverter valve for diverting said exhaust fluid away from said free turbine so that said engine operates as an auxiliary power unit during ground idle.

20. The propulsion system according to claim 15, further comprising a propulsor accessory gear box connected to said free turbine.

21. The propulsion system according to claim 15, further comprising a core accessory gear box connected to said second spool.

22. The propulsion system according to claim 15, wherein said two spool engine comprises a reverse engine core and is a line replaceable unit.

23. The propulsion system according to claim 15, further comprising a starter connected to said first spool and said starter providing initial torque to said first and second spools, whereby said first and second spools rotate at the same speed substantially from rest to said predetermined speed.

24. The propulsion system of claim 23, further comprising said engine having a low pressure compressor having a rotor and said starter being mounted to said rotor of said low pressure compressor.

25. The propulsion system of claim 15, further comprising said engine having a low pressure compressor and a high pressure compressor and said low pressure compressor being larger in size than said high pressure compressor.

26. The propulsion system of claim 25, wherein said engine has a ratio of low pressure compressor pressure ratio to high pressure compressor pressure ratio is in a range of from greater than 2:

1 to 4;

1.