ARCHITECTURE FOR AN AXIALLY COMPACT, HIGH PERFORMANCE PROPULSION SYSTEM

• US 20160290226A1
• Filed: 09/09/2014
• Published: 10/06/2016
• Est. Priority Date: 12/13/2013
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Roberge, Gary D.
• Granted Patent: US 10,550,764 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 13/006 one being a reverse turbine
• 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 3/073 the compressor and turbine stages being concentric
• CPC Class Codes: F02C 3/10 with another turbine driving an output shaft but not driving the compressor
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02K 1/48 Corrugated nozzles
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F02K 3/068 being characterised by a short axial length relative to the diameter
• CPC Class Codes: F02K 3/072 with counter-rotating , e.g. fan rotors
• CPC Class Codes: F02K 3/077 the plant being of the multiple flow type, i.e. having three or more flows
• CPC Class Codes: F02K 3/115 by means of indirect heat exchange
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A reverse-core turbofan engine including a propulsor section including a fan and a fan-tip turbine configured to deliver air to a core duct, including a first portion, disposed aft of the propulsor section, and direct air aft, toward an inlet of a reverse-core gas generator, and a second portion, configured to receive air from an exit of the gas generator and direct the air forward and radially outward of the propulsor, toward the fan-tip turbine in the propulsor, thereby driving the propulsor.

Claims

1. A reverse-core turbofan engine comprising:

a propulsor section including a fan and a fan-tip turbine;

a core duct including;

a first portion, disposed aft of the propulsor section, configured to receive air from the propulsor section, and direct air aft, toward an inlet of a reverse-core gas generator; and

a second portion, configured to receive air from an exit of the reverse-core gas generator and direct the air forward and radially outward of the propulsor, toward the fan-tip turbine in the propulsor, thereby driving the propulsor.

2. The reverse-core turbofan engine of claim 1, wherein the core duct further includes a third portion, configured to receive air from an exit in the fan-tip turbine and direct the air aft, toward an exit of the core duct.

3. The reverse-core turbofan engine of claim 1, wherein the reverse-core gas generator includes a compressor section, a combustor section, and a turbine section.

4. The reverse-core turbofan engine of claim 2, further comprising a bypass duct radially exterior to the inlet of the core duct, and radially interior to the third portion of the core duct.

5. The reverse-core turbofan engine of claim 1, wherein the core duct further comprises at least one hollow strut disposed therein and positioned between the high pressure turbine and the fan-tip turbine.

6. The reverse-core turbofan engine of claim 5, wherein the at least one hollow strut is laterally disposed within the core duct.

7. The reverse-core turbine engine of claim 1, wherein the fan-tip turbine includes a first fan-turbine rotor and a second fan-turbine rotor.

8. The reverse-core turbine engine of claim 7, wherein the first fan-tip turbine is configured to rotate in an opposite direction from the second fan-tip turbine.

9. The reverse-core turbofan engine of claim 3, further comprising a generator device operably coupled to the compressor section.

10. The reverse-core turbofan engine of claim 3, wherein the core duct further comprises a heat exchanger disposed thereon.

11. The reverse-core turbofan engine of claim 10, wherein the heat exchanger is operably coupled to the compressor section

12. The reverse-core turbofan engine of claim 1, further comprising a lobe mixer operably coupled to the exit of the core duct.

13. The reverse-core turbofan engine of claim 3, wherein the fan-tip turbine is fluidly coupled to the compressor section.