Turbocharged compound cycle ducted fan engine system

• US 4,996,839 A
• Filed: 03/29/1989
• Issued: 03/05/1991
• Est. Priority Date: 02/24/1987
• Status: Expired due to Fees

• Current Assignee: Teledyne Technologies Incorporated
• Original Assignee: Teledyne Industries Incorporated (Teledyne Technologies Incorporated)
• Inventors: Wilkinson, Ronald, Benway, Ralph
• Primary Examiner(s): KOCZO JR, MICHAEL
• Application Number:
  US07/329,661
• Time in Patent Office: 706 Days
• Field of Search: 60/598, 60/605, 60/606, 60/612, 60/624, 60/226.1, 60/247, 60/263, 60/269
• US Class Current: 60/247
• CPC Class Codes: F02B 37/005 Exhaust driven pumps being combined with an exhaust driven auxiliary apparatus, e.g. a ventilator
• CPC Class Codes: F02B 37/105 exhaust drive and pump being both connected through gearing to engine-driven shaft
• CPC Class Codes: F02B 39/12 Drives characterised by use of couplings or clutches therein using fluid slip couplings for varying gear ratio F02B39/08
• CPC Class Codes: F02B 41/06 in compound cylinders
• CPC Class Codes: F02C 6/12 Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
• CPC Class Codes: F02K 5/02 the engine being of the reciprocating-piston type
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbocharged, compounded cycle ducted fan engine system includes a conventional internal combustion engine drivingly connected to a fan enclosed in a duct. The fan provides propulsive thrust by accelerating air through the duct and out an exhaust nozzle. A turbocharger is disposed in the duct and receives a portion of the air compressed by the fan. The turbocharger compressor further pressurizes the air and directs it to the internal combustion engine where it is burned and exits as exhaust gas to drive the turbine. A power turbine also driven by exhaust gas is also drivingly connected through the engine to the fan to provide additional power. The size and weight of the turbocharger are reduced since the compressor'"'"'s work is partially achieved by the compression effect of the fan. The total propulsive thrust includes the fan generated thrust which bypasses the turbocharger and the thrust of exhaust gases exiting the turbine.

Claims

1. A propulsion engine system for aircraft comprising:

an internal combustion engine including a rotatable drive shaft, an air inlet and an exhaust outlet;

a fan for generating thrust, said fan being rotatably mounted in a duct and drivingly connected to said drive shaft;

a turbocharger including a turbine having an inlet and an outlet and a compressor having an inlet and an outlet, wherein said turbine is arranged for rotation with said compressor, and said turbine inlet is connected to said exhaust outlet and said compressor outlet is connected to said air inlet of said combustion engine;

means for selectively, drivingly connecting said turbine to said drive shaft including a turbocharger shaft common to said turbine and said compressor, and reduction gearing between said turbocharger shaft and said drive shaft;

wherein said compressor inlet is disposed in said duct downstream from said fan to receive at least a portion of the air thrust from said fan.

2. The invention as defined in claim 1 wherein said internal combustion engine is disposed adjacent said turbocharger.

3. The invention as defined in claim 1 wherein said exhaust outlet and said turbine inlet and intermediate connections are insulated to minimize energy loss.

4. The invention as defined in claim 1 wherein said fan is multistage.

5. The invention as defined in claim 1 wherein said compressor is multistage.

6. The invention as defined in claim 1 wherein said turbine is multistage.

7. The invention as defined in claim 1 and comprising an intercooler disposed between said compressor and said internal combustion engine.

8. The invention as defined in claim 1 and comprising a heat exchanger for cooling said internal combustion engine.

9. The invention as defined in claim 1 wherein said fan and said compressor are coaxial.

10. The invention as defined in claim 1 wherein said turbine is geared directly back into said engine drive shaft.