[특허]Supersonic elliptical ramp inlet

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특허 상세정보

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Supersonic elliptical ramp inlet

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/04 F02K-007/10 B64D-033/02 B64C-030/00
출원번호	US-0586247 (2012-08-15)
등록번호	US-9447731 (2016-09-20)
발명자 / 주소	Adamson, Eric E. Fink, Lawrence E. Fugal, Spencer R.
출원인 / 주소	THE BOEING COMPANY
대리인 / 주소	Patterson + Sheridan, LLP
인용정보	피인용 횟수 : 0 인용 특허 : 6

초록

A supersonic inlet includes a supersonic section including a cowl which is at least partially elliptical, a ramp disposed within the cowl, and a flow inlet disposed between the cowl and the ramp. The ramp may also be at least partially elliptical.

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1. A supersonic inlet comprising: a supersonic compression section comprising a cowl and a ramp;wherein the cowl includes a cowl lip and sides extending from the cowl lip, wherein the cowl lip includes an at least partially elliptical cross-sectional profile as viewed in a first direction along a free stream airflow that is perpendicular to a ramp lip, and wherein the sides are straight between the cowl lip and the ramp lip; andwherein the ramp extends from the ramp lip at an upstream end to at least a throat in the first direction, wherein a flow inlet is an opening between the cowl and the ramp, and the throat is arranged in the flow inlet, wherein the ramp extends between the sides of the cowl in a second direction perpendicular to the first direction, wherein the ramp includes a surface that undulates when traversing the surface from a first point on the ramp along the second direction toward the straight sides of the cowl, such that the surface is convex from the first point on the ramp to second points on the ramp and concave from the second point to the sides, and such that the concave surfaces blend into the straight sides of the cowl. 2. The supersonic inlet of claim 1 wherein the cowl and the ramp form a continuous perimeter around the flow inlet. 3. The supersonic inlet of claim 1 wherein the sides are planar. 4. The supersonic inlet of claim 1 wherein the cowl is U-shaped. 5. The supersonic inlet of claim 1 wherein the supersonic inlet comprises an external-compression supersonic inlet. 6. The supersonic inlet of claim 1 wherein the supersonic inlet comprises a mixed-compression supersonic inlet. 7. The supersonic inlet of claim 1 wherein the ramp comprises two or more turns along the first direction each configured to provide a shock to supersonic air flow flowing through the flow inlet. 8. The supersonic inlet of claim 1 further comprising a subsonic diffusion section attached to the supersonic compression section at a throat, wherein in the supersonic compression section a cross-section of the flow inlet is largest at a beginning entrance of the supersonic inlet and is smallest at the throat, and in the subsonic diffusion section the cross-section of the flow inlet is smallest at the throat and largest at an end of the subsonic diffusion section. 9. The supersonic inlet of claim 8 wherein the subsonic diffusion section is also at least partially elliptical. 10. The supersonic inlet of claim 9 wherein the subsonic diffusion section comprises the cowl and a second ramp disposed within the cowl. 11. The supersonic inlet of claim 10 wherein in the subsonic diffusion section the cowl is at least partially elliptical. 12. The supersonic inlet of claim 1 wherein the supersonic inlet comprises a portion of an aircraft. 13. An aircraft comprising: a supersonic inlet comprising a supersonic compression section attached to a subsonic diffusion section at a throat;wherein the supersonic compression section comprises: a cowl and a first ramp; wherein the cowl includes a cowl lip and sides extending from the cowl lip, wherein the cowl lip includes an at least partially elliptical cross-sectional profile as viewed in a first direction along a free stream airflow that is perpendicular to a ramp lip, and wherein the sides are straight between the cowl lip and the ramp lip;wherein the first ramp extends from the ramp lip at an upstream end to at least a throat in the first direction, wherein a flow inlet is an opening between the cowl and the first ramp, and the throat is arranged in the flow inlet, wherein the first ramp extends between the sides of the cowl in a second direction perpendicular to the first direction, wherein the first ramp includes a surface that undulates when traversing the surface from a first point on the first ramp along the second direction toward the sides of the cowl, such that the surface is convex from the first point on the first ramp to second points on the first ramp and concave from the second points to the sides such that the concave surfaces blend into the straight sides of the cowl; andwherein the subsonic diffusion section comprises: the cowl;a second ramp disposed within the cowl; andthe flow inlet disposed between the cowl and the second ramp. 14. The aircraft of claim 13 wherein the subsonic diffusion section is at least partially elliptical. 15. The aircraft of claim 13, wherein the first ramp comprises two or more turns each configured to provide a shock to supersonic air flow flowing through the flow inlet. 16. A method of diffusing supersonic airflow comprising: flowing supersonic airflow into a flow inlet of a supersonic compression section, the flow inlet disposed between a cowl and a ramp of the supersonic compression section, wherein the cowl includes a cowl lip and sides extending from the cowl lip, wherein the cowl lip includes an at least partially elliptical cross-sectional profile as viewed in a first direction along a free stream airflow that is perpendicular to a ramp lip, and wherein the sides are straight between the cowl lip and the ramp lip, and wherein the ramp extends from the ramp lip at an upstream end to at least a throat in the first direction, wherein the throat is arranged in the flow inlet, wherein the ramp extends between the sides of the cowl in a second direction perpendicular to the first direction, wherein the ramp includes a surface that undulates when traversing the surface from a first point on the ramp along the second direction toward sides of the cowl, such that the surface is convex from the first point on the ramp to second points on the ramp and concave from the second points to the sides, and such that the concave surfaces blend into the straight side surfaces of the cowl; anddiffusing the supersonic airflow as it flows through the flow inlet. 17. The method of claim 16 further comprising flowing the supersonic airflow through a cross-section of the flow inlet which is largest at a beginning entrance of the supersonic compression section and which is smallest at a throat at an end of the supersonic compression section. 18. The method of claim 16 further comprising flowing the supersonic airflow over two or more turns of the ramp along the first direction, with each turn providing a shock to the supersonic air flow. 19. The method of claim 16 further comprising externally compressing the supersonic airflow as it flows through the flow inlet. 20. The method of claim 16 further comprising flowing the supersonic airflow from the supersonic compression section into and through a subsonic diffusion section, and diffusing the supersonic airflow into subsonic airflow within the subsonic diffusion section.

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Supersonic elliptical ramp inlet

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Supersonic elliptical ramp inlet

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