Exhaust systems and methods for gas turbine engine

Patent metadata

Field	Value
Publication number	US-11255239-B2
Application number	US-201816215914-A
Country	US
Kind code	B2
Filing date	Dec 11, 2018
Priority date	May 23, 2016
Publication date	Feb 22, 2022
Grant date	Feb 22, 2022

Abstract

A gas turbine engine includes a combustion section that generates combustive gases that form a primary exhaust flow and an exhaust system downstream from the combustion section. The exhaust system includes an eductor system that includes a body that extends along a first axis, and a plurality of ducts spaced apart about a circumference of the body. Each of the plurality of ducts define a plurality of eductor primary flow paths that terminate in a mixing chamber. The exhaust system includes a muffler system downstream from the mixing chamber that includes a plurality of baffles that cooperate to define a tortuous path and attenuate sound generated by the gas turbine engine. The exhaust system includes a housing that surrounds the eductor system and the muffler system such that the eductor system and the muffler system are contained within the housing.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a combustion section that generates combustive gases that form a primary exhaust flow;
an exhaust system downstream from the combustion section including:
an eductor system configured to receive the primary exhaust flow, the eductor system including a body that extends along a first axis, with a plurality of ducts spaced apart about a circumference of the body, each of the plurality of ducts define a plurality of eductor primary flow paths that terminate in a mixing chamber, and the mixing chamber is adapted to receive a secondary cooling fluid and to mix the primary exhaust fluid with the secondary cooling fluid to create a mixed fluid flow;
a muffler system downstream from the mixing chamber configured to receive the mixed fluid flow from the eductor system, the muffler system including a plurality of baffles that cooperate to define a tortuous path for the mixed fluid flow and attenuate sound generated by the gas turbine engine, the plurality of baffles including a first baffle coupled to a sidewall of a housing and a second baffle spaced apart from the sidewall; and
the housing that surrounds the eductor system and the muffler system such that the eductor system and the muffler system are contained within the housing, the housing having the sidewall, defining an exhaust outlet and including a porous panel that cooperates with the sidewall to define an acoustic chamber about the exhaust outlet, the acoustic chamber spaced apart from the first baffle along the sidewall such that the second baffle is positioned between the first baffle and the acoustic chamber.

2. The gas turbine engine of claim 1 , wherein the porous panel is a perforated panel.

3. The gas turbine engine of claim 1 , wherein the porous panel is a wire screen.

4. The gas turbine engine of claim 1 , wherein the porous panel is a perforated panel that includes a wire screen.

5. The gas turbine engine of claim 1 , wherein the acoustic chamber is filled with a bulk acoustic material.

6. The gas turbine engine of claim 1 , wherein the gas turbine engine extends along a longitudinal axis, and the housing extends along the first axis, which is parallel to the longitudinal axis.

7. The gas turbine engine of claim 1 , wherein the first baffle is a first torus-shaped baffle coupled to the sidewall of the housing, and the second baffle is a second ellipsoid-shaped baffle, and the tortuous path is defined through an opening of the first baffle and about a perimeter of the second baffle.

8. The exhaust system of claim 7 , wherein the first baffle and the second baffle include at least one porous panel and a solid wall that cooperate to define at least one acoustic chamber, and the at least one acoustic chamber is filled with a bulk acoustic material.

9. An aircraft, comprising:
a source of a secondary cooling fluid;
a gas turbine engine including a combustion section that generates combustive gases that form a primary exhaust flow; and
an exhaust system downstream from the combustion section including:
an eductor system that receives the primary exhaust flow, the eductor system including a body that extends along a first axis, with a plurality of ducts spaced apart about a circumference of the body, and each of the plurality of ducts define a plurality of eductor primary flow paths that terminate in a mixing chamber, and the mixing chamber is configured to receive the secondary cooling fluid and to mix the primary exhaust fluid with the secondary cooling fluid to create a mixed fluid flow;
a muffler system downstream from the mixing chamber configured to receive the mixed fluid flow from the eductor system, the muffler system including a plurality of baffles that cooperate to define a tortuous path for the mixed fluid flow and attenuate sound generated by the gas turbine engine; and
a housing that surrounds the eductor system and the muffler system such that the eductor system and the muffler system are contained within the housing and the housing couples the exhaust system to the gas turbine engine.

10. The aircraft of claim 9 , wherein the source of the secondary cooling fluid is an inlet duct defined through a fuselage of the aircraft.

11. The aircraft of claim 9 , wherein the housing is a tail cone.

12. The aircraft of claim 9 , wherein the housing has a first end coupled to the gas turbine engine and an opposite second end, the second end defines an exhaust outlet and the housing includes a porous panel that cooperates with a sidewall of the housing to define an acoustic chamber about the exhaust outlet.

13. The aircraft of claim 12 , wherein the porous panel is a perforated panel or a wire screen and the acoustic chamber is filled with a bulk acoustic material.

14. The aircraft of claim 9 , wherein the gas turbine engine extends along a longitudinal axis, and the housing extends along the first axis, which is parallel to the longitudinal axis.

15. The aircraft of claim 14 , wherein the eductor system directs the mixed fluid flow in a direction transverse to the first axis.

16. The aircraft of claim 9 , wherein the plurality of baffles comprise a first torus-shaped baffle that is coupled to a sidewall of the housing, and a second ellipsoid-shaped baffle, and the tortuous path is defined through an opening of the first baffle and about a perimeter of the second baffle.

17. The aircraft of claim 15 , wherein the plurality of baffles include at least one porous panel and a solid wall that cooperate to define at least one acoustic chamber, and the at least one acoustic chamber is filled with a bulk acoustic material.

Assignees

• Honeywell Int Inc

Inventors

• Shin Yoonshik
• Sheoran Yogendra Yogi
• Brown Daniel

Classifications

• F01D25/30 Primary

  Exhaust heads, chambers, or the like · CPC title

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01N3/05

  by means of air, e.g. by mixing exhaust with air (silencers working by addition of air to exhaust F01N1/14; arrangements for the supply of additional air for the thermal or catalytic conversion of noxious components of exhaust F01N3/30) · CPC title

• F01N1/083 Primary

  using transversal baffles defining a tortuous path for the exhaust gases or successively throttling exhaust gas flow · CPC title