COMPOUND ENGINE ASSEMBLY WITH COMMON INLET

• US 20160245154A1
• Filed: 07/23/2015
• Published: 08/25/2016
• Est. Priority Date: 02/20/2015
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: LAFORTUNE, Serge, THOMASSIN, Jean, BOLDUC, Sebastien, VILLENEUVE, Bruno, BERUBE, Stephane, FONTAINE, Mike, GAGNON-MARTIN, David, JULIEN, Andre, CUNNINGHAM, Mark, LEGARE, Pierre-Yves
• Granted Patent: US 9,797,297 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 2033/0293 for turboprop engines
• CPC Class Codes: B64D 33/02 of combustion air intakes air intakes for gas-turbine plants or jet-propulsion plants per se F02C7/04; air intakes for combustion engines in general F02M35/00
• CPC Class Codes: F01C 1/22 of internal-axis type with equidirectional movement of co-operating members at the points of engagement, or with one of the co-operating members being stationary, the inner member having more teeth or tooth- equivalents than the outer member
• CPC Class Codes: F01C 11/002 of similar working principle
• CPC Class Codes: F01C 11/008 and of complementary function, e.g. internal combustion engine with supercharger
• CPC Class Codes: F01D 13/003 with at least two independent shafts, i.e. cross-compound
• CPC Class Codes: F02B 2053/005 Wankel engines
• CPC Class Codes: F02B 29/0412 Multiple heat exchangers arranged in parallel or in series
• CPC Class Codes: F02B 29/0418 the intake air cooler having a bypass or multiple flow paths within the heat exchanger to vary the effective heat transfer surface
• CPC Class Codes: F02B 29/0493 Controlling the air charge temperature
• CPC Class Codes: F02B 33/34 with rotary pumps with cell-type pressure exchangers or the like F02B33/42
• CPC Class Codes: F02B 41/10 in exhaust turbines use of exhaust turbines for charging F02B37/00
• CPC Class Codes: F02B 53/00 Internal-combustion aspects of rotary-piston or oscillating-piston engines internal-combustion aspects of rotary pistons or outer members for co-operation therewith F02B55/00
• CPC Class Codes: F02B 61/04 for driving propellers
• 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 5/00 Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
• CPC Class Codes: F05D 2220/40 in turbochargers
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies

Abstract

A compound engine assembly including an air conduit having an inlet in fluid communication with ambient air around the compound engine assembly, a compressor having an inlet in fluid communication with the air conduit, an engine core including at least one rotary internal combustion engine and having an inlet in fluid communication with an outlet of the compressor, a turbine section having an inlet in fluid communication with an outlet of the engine core and configured to compound power with the engine core; and at least one heat exchanger in fluid communication with the air conduit, each heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the air conduit circulating therethrough. A method of supplying air to a compound engine assembly is also discussed.

Claims

1. A compound engine assembly comprising:

an air conduit having an inlet in fluid communication with ambient air around the compound engine assembly;

a compressor having an inlet in fluid communication with the air conduit;

an engine core including at least one internal combustion engine each having a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, the engine core having an inlet in fluid communication with an outlet of the compressor;

a turbine section having an inlet in fluid communication with an outlet of the engine core, the turbine section configured to compound power with the engine core; and

at least one heat exchanger in fluid communication with the air conduit, each of the at least one heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the air conduit circulating therethrough.

2. The compound engine assembly as defined in claim 1, wherein the rotor of each of the at least one internal combustion engine has three apex portions separating the rotating chambers and mounted for eccentric revolutions within the respective internal cavity, the respective internal cavity having an epitrochoid shape with two lobes.

3. The compound engine assembly as defined in claim 1, wherein the at least one heat exchanger includes first and second heat exchangers extending in parallel across the air conduit, the first heat exchanger in fluid communication with an oil system of the engine assembly and the second heat exchanger in fluid communication with a coolant system of the engine core.

4. The compound engine assembly as defined in claim 1, wherein the inlet of the air conduit has a lip including a coil tube, the coil tube having an inlet in fluid communication with the coolant system of engine core and an outlet in fluid communication with the second heat exchanger to provide de-icing for the lip.

5. The compound engine assembly as defined in claim 1, wherein the turbine section includes a first stage turbine having an inlet in fluid communication with the outlet of the engine core, and a second stage turbine having an inlet in fluid communication with an outlet of the first stage turbine, the first and second stage turbines have different reaction ratios.

6. The compound engine assembly as defined in claim 1, wherein the inlet of the compressor is in fluid communication with the air conduit through an intake conduit connected to the air conduit upstream of the at least one heat exchanger.

7. The compound engine assembly as defined in claim 6, wherein the air conduit defines a diffuser upstream of the at least one heat exchanger, the intake conduit being connected to the air conduit in the diffuser.

8. The compound engine assembly as defined in claim 1, wherein the inlet of the compressor is in fluid communication with the air conduit through a first intake conduit connected to the air conduit upstream of the at least one heat exchanger and through a second intake conduit connected to the air conduit downstream of the at least one heat exchanger, the assembly further comprising a selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit.

9. A compound engine assembly comprising:

a compressor;

an engine core including at least one rotary internal combustion engine in driving engagement with an engine shaft, the engine core having an inlet in fluid communication with an outlet of the compressor;

a turbine section having an inlet in fluid communication with an outlet of the engine core, the turbine section including at least one turbine rotor engaged on a rotatable turbine shaft, the turbine shaft and the engine shaft being engaged to a same rotatable load;

at least one heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow circulating therethrough; and

a common air conduit having an inlet in fluid communication with ambient air around the compound engine assembly, the common air conduit in fluid communication with an inlet of the compressor and with the at least one heat exchanger.

10. The compound engine assembly as defined in claim 9, wherein each of the at least one rotary internal combustion engine includes a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, the rotor having three apex portions separating the rotating chambers and mounted for eccentric revolutions within the respective internal cavity, the respective internal cavity having an epitrochoid shape with two lobes.

11. The compound engine assembly as defined in claim 9, wherein the at least one heat exchanger includes first and second heat exchangers extending in parallel across the common air conduit, the first heat exchanger in fluid communication with an oil system of the engine assembly and the second heat exchanger in fluid communication with a coolant system of the engine core.

12. The compound engine assembly as defined in claim 11, wherein the inlet of the common air conduit has a lip including a coil tube, the coil tube having an inlet in fluid communication with the coolant system of engine core and an outlet in fluid communication with the second heat exchanger to provide de-icing for the lip.

13. The compound engine assembly as defined in claim 9, wherein the turbine section includes a first stage turbine having an inlet in fluid communication with the outlet of the engine core, and a second stage turbine having an inlet in fluid communication with an outlet of the first stage turbine, the first and second stage turbines have different reaction ratios.

14. The compound engine assembly as defined in claim 9, wherein the inlet of the compressor is in fluid communication with the common air conduit through an intake conduit connected to the air conduit upstream of the at least one heat exchanger.

15. The compound engine assembly as defined in claim 13, wherein the air conduit defines a diffuser upstream of the at least one heat exchanger, the intake conduit being connected to the common air conduit in the diffuser.

16. The compound engine assembly as defined in claim 9, wherein the inlet of the compressor is in fluid communication with the common air conduit through a first intake conduit connected to the air conduit upstream of the at least one heat exchanger and through a second intake conduit connected to the common air conduit downstream of the at least one heat exchanger, the assembly further comprising a selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit.

17. A method of supplying air to a compound engine assembly, the method comprising:

directing ambient air from outside of the compound engine assembly into the compound engine assembly through an inlet of an air conduit;

directing the air from the air conduit through at least one heat exchanger to cool a fluid of the compound engine assembly and from the air conduit to an inlet of a compressor of the compound engine assembly; and

directing compressed air from the compressor into an engine core of the compound engine assembly, the engine core including at least one rotary internal combustion engine creating an exhaust flow driving a turbine section of the compound engine assembly and compounding power with the turbine section to drive rotation of a common load.

18. The method as defined in claim 17, further comprising diffusing the air in the air conduit before directing the air through the at least one heat exchanger and to the inlet of the compressor.

19. The method as defined in claim 17, wherein directing the air through the at least one heat exchanger includes cooling a coolant of the engine core.

20. The method as defined in claim 17, wherein directing the air to the inlet of the compressor is performed from a selected one of a first portion of the air conduit located upstream of the at least one heat exchanger and a second portion of the air conduit located downstream of the at least one heat exchanger.