# US 2014/0360197 A1 · Afterburner and aircraft engine

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- Number: US 2014/0360197 A1
- Document ID: US20140360197A1
- Status: Published application
- Kind: A1
- Application number: 14/470,286
- Filed: 2014-08-27
- Published: 2014-12-11
- Earliest claimed: 2012-03-02
- Assignees: IHI Corporation
- Applicants: IHI Corporation
- Inventors: Shinji TANAKA; Katsuyoshi Takahashi; Jun Hosoi
- Web page: https://patentgrep.com/patent/US20140360197A1

## CPC

- F23R 3/20: incorporating fuel injection means
- F02K 3/11: by means of burners or combustion chambers
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)

## Abstract

An aircraft engine includes an afterburner which has a flame stabilizer. The flame stabilizer maintains a flame generated from a mixed gas of a combustion gas and air. The flame stabilizer includes multiple gutters each configured to generate a flame stabilization area for the flame on its downstream side. Each gutter is formed from: a curved apex section having a stagnation point; and flat plate-shaped side surface sections integrally formed on the respective two sides of the apex section. Each gutter has a V-shaped cross-sectional shape which is opened to the downstream side. At least one through-hole is formed only in each side surface section of each gutter.

## Claims

### Claim 1

An afterburner configured to increase thrust of an aircraft engine by burning a mixed gas of a combustion gas discharged from a core passage of the aircraft engine and air discharged from a fan passage of the aircraft engine again while supplying fuel to the mixed gas, the afterburner comprising:
an outer duct provided to an outlet portion of an engine case of the aircraft engine;
a cylindrical liner provided inside the outer duct, and configured to allow the mixed gas to flow through the liner;
a fuel injector configured to inject the fuel into the liner;
an igniter configured to ignite the mixed gas including the fuel inside the liner; and
a flame stabilizer disposed in a rear of the fuel injector inside the liner, including a plurality of gutters arranged radially and each configured to form a flame stabilization area on a downstream side of the gutter, and configured to hold a flame, wherein
each gutter is formed from a curved apex section and flat plate-shaped side surface sections integrally formed on two sides of the apex section, and has a V-shaped cross- sectional shape which is opened to a downstream side of the gutter, and
at least one through-hole is formed only in each side surface section of the gutter.

### Claim 2 (depends on 1)

The afterburner according to claim 1, wherein a deceleration space for mixing and concurrently decelerating the mixed gas introduced through the at least one through-hole is defined inside the gutter.

### Claim 3 (depends on 1)

An aircraft engine configured to produce thrust by exhausting a mixed gas of a combustion gas and air in a rearward direction, comprising the afterburner according to claim 1.