# US 2014/0196436 A1 · Operation stabilization method and operation stabilization apparatus for supersonic intake

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- Number: US 2014/0196436 A1
- Document ID: US20140196436A1
- Status: Published application
- Kind: A1
- Application number: 14/155,472
- Filed: 2014-01-15
- Published: 2014-07-17
- Earliest claimed: 2013-01-17
- Assignees: Japan Aerospace Exploration Agency
- Applicants: Japan Aerospace Exploration Agency
- Inventors: Yasushi Watanabe
- Web page: https://patentgrep.com/patent/US20140196436A1

## CPC

- F02C 7/042: having variable geometry
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)

## Abstract

An object of the present invention is to provide a technique of enlarging a stable operating range of an intake in accordance with an operating condition of an engine without using a complicated control system so that a wide operating range of the engine can be covered. In an operation stabilization method for a supersonic intake according to the present invention, an enlarged duct between a cowl and a ramp of the intake is divided by a splitter plate such that an opening angle of the enlarged duct decreases. Further, in the operation stabilization method for a supersonic intake according to the present invention, when the duct is divided by the splitter plate, the splitter plate is disposed such that, from among a cowl side duct and a ramp side duct, cross-section variation in one duct, in which an effect of a flow is larger, is reduced within an allowable range of total pressure loss in the other duct.

## Claims

### Claim 1

An operation stabilization method for a supersonic intake, wherein an enlarged duct between a cowl and a ramp of said intake is divided by a splitter plate such that an opening angle of said enlarged duct decreases.

### Claim 2 (depends on 1)

The operation stabilization method for a supersonic intake according to claim 1, wherein, when said duct is divided by said splitter plate, said splitter plate is disposed such that, from among a cowl side duct and a ramp side duct, variation in one duct, in which an effect of a flow is larger, is reduced within an allowable range of total pressure loss in the other duct.

### Claim 3

An operation stabilization apparatus for a supersonic intake, wherein a splitter plate that divides an enlarged duct between a cowl and a ramp of said intake is disposed on a downstream side of a bleed slit such that an opening angle of said enlarged duct decreases.

### Claim 4 (depends on 3)

The operation stabilization apparatus for a supersonic intake according to claim 3, wherein said splitter plate is disposed such that said opening angle of said enlarged duct is equal on said cowl side and said ramp side of said intake.

### Claim 5 (depends on 3)

The operation stabilization apparatus for a supersonic intake according to claim 3, wherein said splitter plate is disposed such that, from among a cowl side duct and a ramp side duct, variation in one duct, in which an effect of a flow is larger, is reduced within an allowable range of total pressure loss in the other duct.