Scramjet engine

Patent metadata

Field	Value
Publication number	US-11215144-B2
Application number	US-201716468996-A
Country	US
Kind code	B2
Filing date	Dec 5, 2017
Priority date	Feb 24, 2017
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

A scramjet engine has a first passage forming member and a second passage forming member. A passage is formed between a first surface and a second surface. The passage has an upstream zone, a combustion zone and a downstream zone. A cavity of a concave shape is provided on the first surface in the combustion zone. The first passage forming member has a convex section located in the upstream zone, a first fuel injection section configured to inject fuel into the passage from a first fuel nozzle provided for the convex section, and a second fuel injection section configured to inject fuel to the cavity. The second passage forming member has a third fuel injection section configured to inject fuel to a direction toward the first surface from the second surface in the passage through a second fuel nozzle provided in the downstream zone.

First claim

The invention claimed is:

1. A scramjet engine comprising:
a first passage forming member having a first surface;
a second passage forming member having a second surface opposing the first surface;
a mixture gas measurement section; and
a fuel injection control section,
wherein a passage is formed between the first surface and the second surface to connect a front opening and a rear opening downstream of the front opening,
wherein the passage comprises:
an upstream zone configured to generate a flow of compressed air obtained by compressing an air taken in through the front opening;
a combustion zone connected downstream of the upstream zone and configured to combust a mixture in which fuel is injected into the flow of compressed air, to generate a combustion gas; and
a downstream zone connected downstream of the combustion zone and configured to exhaust the combustion gas toward the rear opening,
wherein a cavity is provided on the first surface in the combustion zone,
wherein the first passage forming member comprises:
at least one convex section located in the upstream zone and provided on the first surface to protrude toward the second surface from the first surface;
a first fuel injection section configured to inject the fuel into the flow of compressed air through a first fuel nozzle provided for the at least one convex section; and
a second fuel injection section configured to inject the fuel into the cavity,
wherein the second passage forming member comprises a third fuel injection section configured to inject the fuel to a direction toward the first surface from the second surface in the passage through a second fuel nozzle provided on the second surface in the downstream zone,
wherein the mixture gas measurement section is configured to measure a state of the combustion gas in the downstream zone,
wherein the fuel injection control section is configured to control a fuel injection quantity from the third fuel injection section based on the state of the combustion gas measured by the mixture gas measurement section, and
wherein the fuel injection control section is configured to control the third fuel injection section to stop injecting the fuel when the mixture gas measurement section measures that the combustion gas does not contain unburned fuel.

2. The scramjet engine according to claim 1 , wherein the upstream zone has a first region located upstream of the at least one convex section and a second region located downstream of the at least one convex section, and
wherein a height of the passage in a direction orthogonal to the second surface in the second region is higher than a height of the passage in a direction orthogonal to the second surface in the first region.

3. The scramjet engine according to claim 2 , wherein the at least one convex section includes plural convex sections arranged in a direction orthogonal to the flow of compressed air in the first region.

4. The scramjet engine according to claim 1 , wherein a surface of the cavity adjacent to the downstream zone is inclined with respect to the second surface.

5. The scramjet engine according to claim 1 , wherein a cross-sectional area of the passage at a second position downstream of a first position in the downstream zone is greater than that of the passage at the first position in the downstream zone.

6. The scramjet engine according to claim 1 , wherein the first surface is inclined in an angle range of 2° to 4° to the second surface in the downstream zone such that a distance from the second surface to the first surface becomes larger in a downstream direction.

7. The scramjet engine according to claim 1 , wherein an injection direction of the fuel from the third fuel injection section is inclined to an upstream side from a direction orthogonal to the second surface.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Nakamura Masaharu
• Furuya Shojiro
• Hirokane Mariko

Classifications

• F02K7/14 Primary

  with external combustion, e.g. scram-jet engines · CPC title

• F05D2220/10

  in ram-jet engines or ram-jet driven vehicles · CPC title

• F02C9/28

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title

• F05D2270/30

  Control parameters, e.g. input parameters · CPC title