# US 2019/0316546 A1 · Scramjet engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0316546 A1 - Document ID: US20190316546A1 - Status: Published application - Kind: A1 - Application number: 16/468,996 - Filed: 2017-12-05 - Published: 2019-10-17 - Earliest claimed: 2017-02-24 - Assignees: Mitsubishi Heavy Industries, Ltd. - Applicants: Mitsubishi Heavy Industries, Ltd. - Inventors: Masaharu NAKAMURA; Shojiro FURUYA; Mariko HIROKANE - Web page: https://patentgrep.com/patent/US20190316546A1 ## CPC - F02K 7/14: with external combustion, e.g. scram-jet engines - F02C 9/28: Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) - F05D 2220/10: in ram-jet engines or ram-jet driven vehicles - F05D 2270/30: Control parameters, e.g. input parameters - 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) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A scramjet engine has first and second passage forming members. A passage is formed between the first surface and the 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 which injects the fuel into the passage from a fuel nozzle provided for the convex section, and a second fuel injection section which injects the fuel to the cavity. The second passage forming member has a third fuel injection section which injects the fuel to a direction toward the first surface from the second surface in the passage through the second fuel nozzle provided in the downstream zone. ## Claims ### Claim 1 A scramjet engine comprising: a first passage forming member having a first surface; and a second passage forming member having a second surface opposing to the first surface, wherein a passage is formed between the first surface and the second surface to connect a front opening and a rear opening provided 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 to the flow of compressed air through a first fuel nozzle provided for the convex section; and a second fuel injection section configured to inject the fuel to the cavity, and 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. ### Claim 2 (depends on 1) The scramjet engine according to claim 1, wherein the upstream zone has a first region located upstream of the convex section and a second region located downstream of the convex section, and wherein a height of the passage in a direction orthogonal to the second surface in the first region is higher than a height of the passage in a direction orthogonal to the second surface in the second region. ### Claim 3 (depends on 2) The scramjet engine according to claim 2, wherein a plurality of the convex sections are arranged in a direction orthogonal to the flow of compressed air in the first region. ### Claim 4 (depends on 1) The scramjet engine according to claim 1, wherein a surface of the cavity situated adjacently to the downstream zone is inclined with respect to the second surface. ### Claim 5 (depends on 1) 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. ### Claim 6 (depends on 1) 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. ### Claim 7 (depends on 1) 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. ### Claim 8 (depends on 1) The scramjet engine according to claim 1, further comprising: a mixture gas measurement section configured to measure a state of combustion gas in the downstream zone; and a fuel injection control section configured to control a fuel injection quantity from the third fuel injection section based on the measured state of combustion gas. ### Claim 9 (depends on 8) The scramjet engine according to claim 8, wherein, when the mixture gas measurement section measures that the combustion gas does not contain unburned fuel, the fuel injection control section controls the third fuel injection section to stop the fuel injection.