# US 5,349,815 A · Scramjet combustor having a two-part, aft-facing step > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 5,349,815 A - Document ID: US5349815A - Status: Granted - Kind: A - Application number: 07/750,343 - Filed: 1991-08-27 - Granted: 1994-09-27 - Earliest claimed: 1991-08-27 - Assignees: General Electric Company - Inventors: Paul H. Kutschenreuter, Jr. - Web page: https://patentgrep.com/patent/US5349815A ## CPC - F02K 7/10: characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines - 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 A flight vehicle scramjet combustor. The combustor, in its "2-D" and annular embodiments, has two spaced-apart, generally opposing, and longitudinally extending walls. One wall includes a generally aft-facing step having a first section and an interconnected second section, a forward wall portion attached to the first section, and an aft wall portion attached to the second section. The second section includes a fuel injector discharge orifice having a fuel discharge axis which is aligned generally perpendicular to the second section and which projects both generally towards the other wall and longitudinally aft. The combustor has a cylindrical embodiment which includes a cylindrical wall having a step and fuel injector discharge orifice similar those of the "2-D" and annular combustor embodiments. ## Claims ### Claim 1 A flight vehicle scramjet combustor comprising: two spaced-apart, generally opposing, and generally longitudinally extending walls extending forward and aft, wherein one of said walls includes a generally aft-facing step, a forward wall portion extending generally longitudinally forward of said step, and an aft wall portion extending generally longitudinally aft of said step, wherein said step includes a first section and an interconnected second section, wherein said first section is attached to said forward wall portion and said second section is attached to said aft wall portion, and wherein said first section is generally perpendicular to said forward wall portion and said second section includes a fuel injector discharge orifice and faces both generally towards the other of said walls and longitudinally aft. ### Claim 2 (depends on 1) The combustor of claim 1, wherein said one wall has a generally annular shape longitudinally forward of said step and a generally annular shape longitudinally aft of said step. ### Claim 3 (depends on 1) The combustor of claim 1, wherein said one wall has a generally planar shape longitudinally forward of said step and a generally planar shape longitudinally aft of said step. ### Claim 4 (depends on 1) The combustor of claim 1, wherein said fuel injector discharge orifice has a generally rectangular shape with two longer sides and two shorter sides, wherein said first and second sections intersect along an intersection, and wherein said two shorter sides are each generally parallel to said intersection. ### Claim 5 (depends on 4) The combustor of claim 4, wherein said one wall has a generally planar shape longitudinally forward of said step and a generally planar shape longitudinally aft of said step. ### Claim 6 (depends on 5) The combustor of claim 5, wherein said forward wall portion and said first section intersect along a generally straight line having a first end and a second end and wherein said first end is disposed longitudinally forward of said second end. ### Claim 7 (depends on 6) The combustor of claim 6, wherein said second section also includes additional said fuel injector discharge orifices spaced apart from themselves and from said fuel injector discharge orifice. ### Claim 8 (depends on 7) The combustor of claim 7, wherein said fuel injector discharge orifice and said additional said fuel injector discharge orifices are generally aligned in a row. ### Claim 9 (depends on 8) The combustor of claim 8, wherein said other wall includes a step having spaced apart fuel injector discharge orifices which are not aligned with any of those of said one wall. ### Claim 10 (depends on 1) The combustor of claim 1, wherein said one wall includes a second step disposed longitudinally aft of said step. ### Claim 11 (depends on 1) The combustor of claim 1, wherein said other wall includes a step. ### Claim 12 (depends on 11) The combustor of claim 11, wherein said step of said one wall is disposed longitudinally forward of said step of said other wall. ### Claim 13 A flight vehicle scramjet combustor comprising: a longitudinal axis and a generally coaxially disposed cylindrical wall extending generally longitudinally forward and aft, said wall including a generally aft-facing step, a forward wall portion extending generally longitudinally forward of said step, and an aft wall portion extending generally longitudinally aft of said step, wherein said step includes a first section and an interconnected second section, wherein said first section is attached to said forward wall portion and said second section is attached to said aft wall portion, and wherein said first section is generally perpendicular to said forward wall portion and said second section includes a fuel injector discharge orifice and faces both generally towards said longitudinal axis and longitudinally aft. ### Claim 14 (depends on 13) The combustor of claim 13, wherein said wall has a generally annular shape longitudinally forward of said step and a generally annular shape longitudinally aft of said step. ### Claim 15 (depends on 13) The combustor of claim 13 wherein said fuel injector discharge orifice has a generally rectangular shape with two longer sides and two shorter sides, wherein said first and second sections intersect along an intersection, and wherein said two shorter sides are each generally parallel to said intersection.