REVERSE FLOW GAS TURBINE ENGINE AIRFLOW BYPASS

• US 20140250862A1
• Filed: 02/26/2014
• Published: 09/11/2014
• Est. Priority Date: 03/07/2013
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Suciu, Gabriel L., Merry, Brian D.
• Granted Patent: US 9,726,112 B2
• Time in Patent Office: Days
• US Class Current: 60/224
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2210/40 Flow geometry or direction
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine has a propulsor including a fan and a power turbine, an engine core aerodynamically connected to the propulsor by a transition duct, and a bypass valve in the transition duct that allows for air from the engine core to bypass the power turbine.

Claims

1. A gas turbine engine comprising:

a propulsor including a fan and a power turbine;

an engine core aerodynamically connected to the propulsor by a transition duct; and

a bypass valve in the transition duct that allows for air from the engine core to bypass the power turbine.

2. The gas turbine engine of claim 1, wherein the engine core includes a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section.

3. The gas turbine engine of claim 2, wherein the propulsor delivers air into the compressor section through a flow inlet duct.

4. The gas turbine engine of claim 3, wherein the engine core is attached to the transition duct and flow inlet duct.

5. The gas turbine engine of claim 1, wherein the propulsor has a first axis and the engine core has a second axis.

6. The gas turbine engine of claim 5, wherein the first axis and second axis are not parallel.

7. The gas turbine engine of claim 6, wherein the power turbine is positioned downstream of the turbine section of the engine core;

and further comprising;

a gear reduction between the power turbine and the fan of the propulsor to cause the fan to rotate at a slower speed than the power turbine.

8. The gas turbine engine of claim 7, wherein the power turbine rotates on the first axis.

9. The gas turbine engine of claim 1, wherein the bypass valve is a butterfly valve.

10. An aircraft comprising:

an aircraft body;

an engine attached to the aircraft body including;

a propulsor having a fan and a power turbine;

an engine core aerodynamically connected to the propulsor by a transition duct; and

an airflow bypass in the transition duct that allows for airflow from the engine core to bypass the power turbine.

11. The aircraft of claim 10, wherein the engine core includes a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section.

12. The aircraft of claim 11, wherein the propulsor delivers air into the compressor section through a flow inlet duct.

13. The aircraft of claim 12, wherein the engine core is attached to the transition duct and flow inlet duct.

14. The aircraft of claim 10, wherein the propulsor has a first axis and the engine core has a second axis.

15. The aircraft of claim 14, wherein the first axis and second axis are not parallel.

16. The aircraft of claim 15, wherein the power turbine is positioned downstream of the turbine section of the engine core;

and further comprising;

a gear reduction between the power turbine and the fan of the propulsor to cause the fan to rotate at a slower speed than the power turbine.

17. The aircraft of claim 16, wherein the power turbine rotates on the first axis.

18. The aircraft of claim 10, wherein the airflow bypass is a valve.

19. The aircraft of claim 18 wherein the valve is a butterfly valve.

20. A gas turbine engine comprising:

a propulsor;

a gas generator aerodynamically connected to the propulsor by a transition duct; and

an airflow bypass in the transition duct that allows for the venting of airflow from the engine core to bypass the propulsor.