REVERSE FLOW GAS TURBINE ENGINE REMOVABLE CORE

• US 20140252160A1
• Filed: 02/26/2014
• Published: 09/11/2014
• Est. Priority Date: 03/07/2013
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Suciu, Gabriel L., Merry, Brian D.
• Application Number:
  US14/190,150
• Publication Number:
  US 20140252160A1
• Time in Patent Office: Days
• US Class Current: 244/55
• CPC Class Codes: B64D 27/12 within, or attached to, wings
• CPC Class Codes: F02C 3/10 with another turbine driving an output shaft but not driving the compressor
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02K 3/077 the plant being of the multiple flow type, i.e. having three or more flows
• CPC Class Codes: F05D 2210/40 Flow geometry or direction
• CPC Class Codes: F05D 2230/50 Building or constructing in particular ways
• CPC Class Codes: F05D 2230/72 Maintenance
• CPC Class Codes: F05D 2250/30 Arrangement of components
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: Y10T 29/49721 with disassembling

Abstract

An engine mounting arrangement includes a propulsor mounted to an aircraft wing, and an engine core aerodynamically connected to the propulsor and positioned rearward of the propulsor.

Claims

1. An engine mounting arrangement comprising:

a propulsor attached to an aircraft wing;

an engine core aerodynamically connected to the propulsor for driving the propulsor with an exhaust flow, and positioned rearward of the propulsor.

2. The engine mounting arrangement 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 engine mounting arrangement of claim 2, wherein the propulsor and engine core are connected by a transition duct.

4. The engine mounting arrangement of claim 3, wherein the propulsor delivers air into the compressor section through a flow inlet duct.

5. The engine mounting arrangement of claim 4, wherein the engine core is attached to the transition duct and flow inlet duct.

6. The engine mounting arrangement of claim 2, wherein the propulsor has a first axis and the engine core has a second axis.

7. The engine mounting arrangement of claim 6, wherein the first axis and second axis are not parallel.

8. The engine mounting arrangement of claim 1, wherein the propulsor is housed in a nacelle.

9. The engine mounting arrangement of claim 8, wherein the propulsor comprises:

a fan;

a power turbine; and

a shaft connecting the power turbine to the fan.

10. An aircraft comprising:

a fuselage;

a wing attached to the fuselage; and

an engine mounted to the wing, the engine including;

a propulsor mounted to an aircraft wing; and

an engine core aerodynamically connected to the propulsor.

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 and engine core are connected by a transition duct.

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

14. The aircraft of claim 15, wherein the engine core is attached to the transition duct and flow inlet duct.

15. The aircraft of claim 16, wherein the propulsor has a first axis and the engine core has a second axis.

16. The aircraft of claim 17, wherein the first axis and second axis are not parallel.

17. The aircraft of claim 10, wherein the propulsor is housed in a nacelle.

18. The aircraft of claim 17, wherein the propulsor comprises:

a fan;

a power turbine; and

a shaft connecting the power turbine to the fan.

19. A method of overhauling an engine, the method comprising:

removing an engine core aerodynamically connected to a propulsor, wherein the propulsor is attached to an aircraft wing and remains on the aircraft wing during overhaul of the engine core.

20. The method of claim 19 wherein the engine core is a reverse core that includes a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section.