Exhaust duct for turbine forward of fan

Patent metadata

Field	Value
Publication number	US-10267263-B2
Application number	US-201615230590-A
Country	US
Kind code	B2
Filing date	Aug 8, 2016
Priority date	Aug 8, 2016
Publication date	Apr 23, 2019
Grant date	Apr 23, 2019

Abstract

A gas turbine engine includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A propulsor section aft of the core engine is driven by the turbine section. An exhaust duct routing exhaust gases around the propulsor section. The exhaust duct includes an inlet forward of the propulsor section, an outlet aft of the turbine section and a passageway between the inlet and the outlet. An aircraft and exhaust duct are also disclosed.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section, wherein the turbine section is coupled to drive the compressor section;
a drive shaft driven by the turbine section of the core engine;
a propulsor section aft of the core engine driven by the drive shaft; and
an exhaust duct routing exhaust gases around the propulsor section, the exhaust duct including an inlet forward of the propulsor section, an outlet aft of the turbine section and a passageway between the inlet and the outlet, wherein the exhaust duct is routed such that exhaust gases are not in communication with the drive shaft.

2. The gas turbine engine as recited in claim 1 , wherein the outlet is aft of the propulsor section.

3. The gas turbine engine as recited in claim 1 , wherein the inlet is transverse to an axis of the core engine and open 360 degrees about the axis of the core engine and the outlet defines an opening spaced radially apart from the engine axis.

4. The gas turbine engine as recited in claim 3 , wherein the outlet is disposed below the engine axis and includes a width greater than a height.

5. The gas turbine engine as recited in claim 1 , wherein the outlet comprises a first outlet spaced apart from a second outlet and the passageway comprises a first passageway between the inlet and the first outlet and a second passageway between the inlet and the second outlet.

6. The gas turbine engine as recited in claim 5 , wherein the first outlet is disposed on one side of the propulsor and the second outlet is disposed on a second side of the propulsor.

7. The gas turbine engine as recited in claim 1 , including a free turbine aft of the turbine section, the drive shaft coupled to the free turbine.

8. The gas turbine engine as recited in claim 1 , including a gearbox driven by the drive shaft, wherein the propulsor includes at least one ducted fan driven by a propulsor shaft driven by the gearbox.

9. The gas turbine engine as recited in claim 1 , wherein the core engine section is mounted within an aircraft fuselage and the propulsor section is disposed at an aft section of the aircraft fuselage.

10. An aircraft comprising:
a core engine assembly supported within an aircraft fuselage, the core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section;
an air intake within the aircraft fuselage communicating air to the core engine assembly;
a drive shaft driven by the turbine section of the core engine;
a propulsor section aft of the core engine assembly and mounted to an aft section of the aircraft fuselage, the propulsors section driven by the drive shaft; and
an exhaust duct routing exhaust gases from the turbine section around the propulsor section and through the aircraft fuselage, the exhaust duct including an inlet opening forward of the propulsor section, an outlet aft of the propulsor section and a passageway between the inlet opening and the outlet.

11. The aircraft as recited in claim 10 , wherein the inlet opening is transverse to an axis of the core engine and open 360 degrees about the axis of the core engine and the outlet defines an opening spaced radially apart from the engine axis.

12. The aircraft as recited in claim 10 , wherein the outlet comprises a first outlet spaced apart from a second outlet and the passageway comprises a first passageway between the inlet opening and the first outlet and a second passageway between the inlet opening and the second outlet.

13. The aircraft as recited in claim 12 , wherein the first outlet is disposed on one side of the propulsor and the second outlet is disposed on a second side of the propulsor.

14. The aircraft as recited in claim 10 , wherein the exhaust duct is routed such that exhaust gases do not impinge on the drive shaft.

15. The aircraft as recited in claim 14 , including a gearbox driven by the drive shaft, wherein the propulsor includes at least one ducted fan driven by a propulsor shaft driven by the gearbox.

16. An exhaust duct for routing exhaust from a turbine forward of a fan, the exhaust duct comprising:
an inlet opening disposed proximate a turbine outlet, the inlet opening disposed 360 degrees about an engine axis;
a passageway spaced apart from the engine axis and extending aft from the inlet opening;
a split portion aft of the inlet opening splitting the passageway around the engine axis; and
an outlet opening disposed aft of a fan such that exhaust flow is routed away from the fan.

17. The exhaust duct as recited in claim 16 , wherein the outlet comprises a rectangular opening aft of the fan and below the engine axis relative to the split portion.

18. The exhaust duct as recited in claim 16 , wherein the outlet comprises a first outlet spaced apart from a second outlet and the passageway comprises a first passageway between the inlet opening and the first outlet and a second passageway between the inlet opening and the second outlet.

Assignees

• United Technologies Corp

Inventors

• Lord Wesley K
• Chandler Jesse M
• Suciu Gabriel L

Classifications

• B64D35/04 Primary

  characterised by the transmission driving a plurality of propellers or rotors · CPC title

• F02K3/00 Primary

  Plants including a gas turbine driving a compressor or a ducted fan · CPC title

• F02K1/52

  Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing · CPC title

• F02K3/062

  with aft fan · CPC title

• B64D33/02

  of combustion air intakes · CPC title