Compound engine assembly with exhaust pipe nozzle

Patent metadata

Field	Value
Publication number	US-9759128-B2
Application number	US-201514740889-A
Country	US
Kind code	B2
Filing date	Jun 16, 2015
Priority date	Jun 16, 2015
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.

First claim

The invention claimed is:

1. A compound engine assembly comprising:
an engine core including at least one internal combustion engine defining an internal cavity and including a rotor sealingly and rotationally received within the internal cavity to provide rotating chambers of variable volume in the internal cavity, the variable volume varying between a minimum volume and a maximum volume with a difference between the maximum and minimum volumes defining a displacement volume Vd;
a turbine configured as an impulse turbine having a pressure based reaction ratio of at most 0.25, the turbine including a rotor including a circumferential array of rotor blades extending across a flow path; and
an exhaust pipe having a pipe volume Vp, the exhaust pipe providing fluid communication between an exhaust port of the at least one internal combustion engine and the flow path of the turbine, the exhaust pipe terminating in a nozzle communicating with a portion of the flow path located upstream of the rotor blades;
wherein a ratio Vp/Vd between the pipe volume Vp of the exhaust pipe and the displacement volume Vd of the at least one internal combustion engine is at most 1.5; and
wherein a minimum value of a cross-sectional area of the exhaust pipe is defined at the nozzle.

2. The compound engine assembly as defined in claim 1 , wherein the rotor of the turbine and the rotor of the at least one internal combustion engine are in driving engagement with a common load.

3. The compound engine assembly as defined in claim 1 , wherein the ratio Vp/Vd is at most 1.0.

4. The compound engine assembly as defined in claim 1 , wherein the cross-sectional area of the exhaust pipe upstream of the nozzle is constant.

5. The compound engine assembly as defined in claim 4 , wherein the cross-sectional area of the exhaust pipe upstream of the nozzle corresponds to a cross-sectional area of the exhaust port of the at least one internal combustion engine.

6. The compound engine assembly as defined in claim 5 , wherein the ratio An/Ae is at most 0.6.

7. The compound engine assembly as defined in claim 1 , wherein a ratio An/Ae between the minimum value An of the cross-sectional area at the nozzle of the exhaust pipe and a cross-sectional area Ae of the exhaust port of the at least one internal combustion engine is at least 0.2.

8. The compound engine assembly as defined in claim 5 , wherein the ratio An/Ae is at least 0.4.

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

10. The compound engine assembly as defined in claim 1 , wherein the turbine is a first stage turbine, the assembly further comprising a turbocharger including a compressor and a second stage turbine in driving engagement with one another, an outlet of the compressor being in fluid communication with an inlet port of the at least one internal combustion engine, and an inlet of the second stage turbine being in fluid communication with a portion of the flow path of the first stage turbine located downstream of the rotor blades of the first stage turbine, the second stage turbine having a pressure based reaction ratio higher than that of the first stage turbine.

11. The compound engine assembly as defined in claim 1 , wherein the at least one internal combustion engine includes first and second internal combustion engines, the nozzle of the exhaust pipe of the first internal combustion engine being spaced apart from the nozzle of the exhaust pipe of the second internal combustion engine along a circumferential direction of the turbine.

12. The compound engine assembly as defined in claim 1 , further comprising a heavy fuel source in communication with the at least one internal combustion engine.

13. A compound engine assembly comprising:
an engine core including at least one internal combustion engine defining an internal cavity and including a rotor sealingly and rotationally received within the internal cavity to provide rotating chambers of variable volume in the internal cavity, and having an inlet port and an exhaust port in communication with the internal cavity, the exhaust port having a cross-sectional area Ae;
a turbine configured as an impulse turbine having a pressure based reaction ratio of at most 0.25, the turbine including a rotor having a circumferential array of rotor blades extending across a flow path; and
an exhaust pipe providing fluid communication between the exhaust port of the at least one internal combustion engine and the flow path of the turbine, the exhaust pipe terminating in a nozzle communicating with a portion of the flow path located upstream of the rotor blades;
wherein the nozzle of the exhaust pipe includes a portion of reduced cross-sectional area with respect to a remainder of the exhaust pipe, the nozzle defining a minimum cross-sectional area An of the exhaust pipe; and
wherein a ratio An/Ae between the minimum cross-sectional area An of the exhaust pipe and the cross-sectional area Ae of the exhaust port of the at least one internal combustion engine is at least 0.2.

14. The compound engine assembly as defined in claim 13 , wherein the rotor of the turbine and the rotor of the at least one internal combustion engine are in driving engagement with a common load.

15. The compound engine assembly as defined in claim 13 , wherein the cross-sectional area of the exhaust pipe upstream of the nozzle is constant.

16. The compound engine assembly as defined in claim 15 , wherein the cross-sectional area of the exhaust pipe upstream of the nozzle corresponds to the cross-sectional area Ae of the exhaust port of the at least one internal combustion engine.

17. The compound engine assembly as defined in claim 13 , wherein the ratio An/Ae is at most 0.6.

18. The compound engine assembly as defined in claim 17 , wherein the ratio An/Ae is at least 0.4.

19. The compound engine assembly as defined in claim 13 , wherein the at least one internal combustion engine is at least one Wankel engine, the rotor having three apex portions separating the rotating chambers and mounted for eccentric revolutions within the internal cavity, the internal cavity having an epitrochoid shape with two lobes.

20. The compound engine assembly as defined in claim 13 , wherein the turbine is a first stage turbine, the assembly further comprising a turbocharger including a compressor and a second stage turbine in driving engagement with one another, an outlet of the compressor being in fluid communication with the inlet port of the at least one internal combustion engine, and an inlet of the second stage turbine being in fluid communication with a portion of the flow path of the first stage turbine located downstream of the rotor blades of the first stage turbine, the second stage turbine having a pressure based reaction ratio higher than that of the first stage turbine.

21. The compound engine assembly as defined in claim 13 , further comprising a heavy fuel source in communication with the at least one internal combustion engine.

22. A method of compounding at least one rotary engine, the method comprising:
providing a turbine configured as an impulse turbine having a pressure based reaction ratio of at most 0.25;
drivingly engaging the at least one rotary engine

Assignees

• Pratt & Whitney Canada

Inventors

• Julien Andre
• Dussault Serge
• Bilodeau Jade
• Besner Renaud

Classifications

• F01C1/22 Primary

  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 title

• F01C11/002

  of similar working principle · CPC title

• F01C11/008

  and of complementary function, e.g. internal combustion engine with supercharger · CPC title

• F02C6/12

  Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure · CPC title

• F02C5/00

  Gas-turbine plants characterised by the working fluid being generated by intermittent combustion · CPC title