Propulsion system for jet noise reduction

Patent metadata

Field	Value
Publication number	US-12339002-B2
Application number	US-202217732888-A
Country	US
Kind code	B2
Filing date	Apr 29, 2022
Priority date	Apr 29, 2022
Publication date	Jun 24, 2025
Grant date	Jun 24, 2025

Abstract

A propulsion system is provided, wherein the propulsion system includes an afterburner assembly. The afterburner assembly including: an exhaust section and a fuel injector assembly that is operable to inject fuel in the exhaust section. The fuel injector assembly includes a plurality of fuel injection members. The plurality of fuel injection members defines a hot zone and a cold zone. The cold zone is positioned to provide a noise insulation barrier for the hot zone.

First claim

What is claimed is:

1. A propulsion system comprising:
a turbomachine; and
an afterburner assembly disposed downstream of the turbomachine, the afterburner assembly comprising:
an exhaust section; and
a fuel injector assembly positioned within the exhaust section, the fuel injector assembly comprising a plurality of fuel injection members and a flame stability device, the plurality of fuel injection members each spaced circumferentially apart, each fuel injection member extending radially inward, the plurality of fuel injection members each operable for injecting fuel in the exhaust section, wherein during operation in a full thrust condition of the propulsion system and the plurality of fuel injection members a hot zone and a cold zone are defined by an injection rate of the fuel into the exhaust section via the plurality of fuel injection members, wherein the cold zone is positioned radially outward of the hot zone, wherein during operation of the propulsion system and the plurality of fuel injection members a noise insulation barrier for the hot zone is provided by the cold zone, wherein during operation in the full thrust condition, the cold zone radially shields noise generated by the hot zone thereby reducing external noise produced by the afterburner assembly, wherein the fuel injector assembly is operable to modify a fuel injection rate of the plurality of fuel injection members, wherein the flame stability device comprises a first flame stability device positioned downstream of the plurality of fuel injection members and a second flame stability device positioned downstream of the plurality of fuel injection members, and wherein the first flame stability device has a first configuration and the second flame stability device has a second configuration different than the first configuration.

2. The propulsion system of claim 1 , wherein the flame stability device includes a central ring having a plurality of inner radial gutters and a plurality of outer radial gutters, wherein the plurality of inner radial gutters and the plurality of outer radial gutters each include a side wall, a leading edge, and a wake region, and wherein each of the plurality of inner radial gutters and each of the plurality of outer radial gutters define a generally V-shaped cross section.

3. The propulsion system of claim 2 , wherein the plurality of fuel injection members comprises a first fuel injection member, the first fuel injection member comprising a first set of fuel nozzles and a second set of fuel nozzles, the first set of fuel nozzles positioned in the cold zone, the second set of fuel nozzles positioned in the hot zone, wherein the fuel injector assembly is operable to control a fuel injection rate of the first set of fuel nozzles relative to a fuel injection rate of the second set of fuel nozzles, and wherein the second set of fuel nozzles are larger than the first set of fuel nozzles.

4. The propulsion system of claim 2 , wherein the first flame stability device and the second flame stability device each include a v-gutter flame holder, h-gutter flame holder, ring flame holder, or a plurality of flame holders.

5. The propulsion system of claim 1 , wherein the afterburner assembly is a first afterburner assembly, wherein the fuel injector assembly is a first fuel injector assembly, wherein the plurality of fuel injection members is a first plurality of fuel injection members, wherein the propulsion system further comprises a second afterburner assembly having a second fuel injector assembly, wherein the second fuel injector assembly comprises a second plurality of fuel injection members defining a hot zone and a cold zone.

6. The propulsion system of claim 5 , wherein the cold zone of the second afterburner assembly is positioned to provide a noise insulation barrier for the hot zone of the second afterburner assembly.

7. The propulsion system of claim 5 , wherein the hot zone of the first afterburner assembly and the hot zone of the second afterburner assembly are adjacent.

8. The propulsion system of claim 1 , wherein the fuel injector assembly defines a first average temperature within the cold zone during an operating condition of the propulsion system, wherein the fuel injector assembly defines a second average temperature within the hot zone during the operating condition of the propulsion system, and wherein the first average temperature is at least 10% lower than the second average temperature.

9. The propulsion system of claim 1 , wherein the propulsion system defines an axial direction,
wherein the propulsion system defines a crosswise plane perpendicular to the axial direction, and wherein the hot zone and the cold zone are defined in the crosswise plane.

Assignees

• Gen Electric

Inventors

• Pastouchenko Nikolai N
• Paliath Umesh
• Yoon Changjin
• Lee Jason A
• Perveiler David Andrew

Classifications

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F02K3/10 Primary

  by after-burners (F02K3/105 takes precedence) · CPC title

• F23R3/20 Primary

  incorporating fuel injection means · CPC title