Air inlet arrangement and method of making the same
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/04
F02C-007/045
B64D-033/02
F02K-007/10
F02K-007/16
F02K-007/20
F02K-001/04
F02K-001/46
F02C-007/00
F02K-007/00
F02K-003/02
출원번호
US-0541482
(2012-07-03)
등록번호
US-9353704
(2016-05-31)
발명자
/ 주소
Conners, Timothy R.
Henne, Preston A.
Howe, Donald C.
출원인 / 주소
Gulfstream Aerospace Corporation
대리인 / 주소
Ingrassia, Fisher & Lorenz PC
인용정보
피인용 횟수 :
1인용 특허 :
2
초록▼
An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is
An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.
대표청구항▼
1. An air inlet arrangement for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the air inlet arrangement comprising: a cowl having a co
1. An air inlet arrangement for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the air inlet arrangement comprising: a cowl having a cowl lip; and a center body coaxially aligned with the cowl, the center body having an apex, a first compression surface downstream of the apex, and a second compression surface downstream of the first compression surface, the second compression surface being spaced apart from the cowl lip such that the second compression surface and the cowl lip define an inlet,wherein a protruding portion of the center body extends upstream of the cowl lip and wherein the protruding portion of the center body is configured to displace a portion of a column of air disposed upstream of the center body and longitudinally aligned therewith, the column of air having a periphery defined by a leading edge of the cowl, the portion of the column of air being displaced out of the path of the inlet by the protruding portion of the center body such that a remaining sub-portion of the column of air at an upstream boundary of a terminal shock of the inlet is not greater than an amount of air that can be consumed by the supersonic jet engine when the supersonic jet engine consumes air at the predetermined mass flow rate while the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed. 2. The air inlet arrangement of claim 1, wherein the cowl lip is oriented at an angle substantially parallel to a direction of a free stream. 3. The air inlet arrangement of claim 1, wherein the inlet has an annular configuration. 4. The air inlet arrangement of claim 1, further comprising an expansion surface disposed between the first compression surface and the second compression surface. 5. The air inlet arrangement of claim 4, wherein the first compression surface is contiguous with the expansion surface and wherein the expansion surface is contiguous with the second compression surface. 6. The air inlet arrangement of claim 1, wherein the second compression surface is an isentropic compression surface. 7. The air inlet arrangement of claim 1, wherein the second compression surface is a relaxed isentropic compression surface. 8. An air inlet arrangement for use with a supersonic jet engine configured to consume air at a first predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the air inlet arrangement comprising: a cowl having a cowl lip; a center body coaxially aligned with the cowl, the center body having an apex, a first compression surface downstream of the apex, and a second compression surface downstream of the first compression surface, the second compression surface being spaced apart from the cowl lip such that the second compression surface and the cowl lip define an inlet; anda bypass splitter disposed between the cowl and the center body to form a bypass configured to receive air at a second predetermined mass flow rate when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed,wherein a protruding portion of the center body extends upstream of the cowl lip and wherein the protruding portion of the center body is configured to displace a portion of a column of air disposed upstream of the center body and longitudinally aligned therewith, the column of air having a periphery defined by a leading edge of the cowl, the portion of the column of air being displaced out of the path of the inlet by the protruding portion of the center body such that a remaining sub-portion of the column of air at an upstream boundary of a terminal shock of the inlet is not greater than an amount of air that can be consumed by the supersonic jet engine and the bypass, combined, when the supersonic jet engine consumes air at the first predetermined mass flow rate and when the bypass consumes air at the second predetermined mass flow rate while the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed. 9. The air inlet arrangement of claim 8, wherein the cowl lip is oriented at an angle substantially parallel to a direction of a free stream. 10. The air inlet arrangement of claim 8, wherein the inlet has an annular configuration. 11. The air inlet arrangement of claim 8, further comprising an expansion surface disposed between the first compression surface and the second compression surface. 12. The air inlet arrangement of claim 11, wherein the first compression surface is contiguous with the expansion surface and wherein the expansion surface is contiguous with the second compression surface. 13. The air inlet arrangement of claim 8, wherein the second compression surface is an isentropic compression surface. 14. The air inlet arrangement of claim 8, wherein the second compression surface is a relaxed isentropic compression surface. 15. A method of making an air inlet arrangement for use with a supersonic jet engine configured to consume air at a first predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the method comprising the steps of: providing a cowl and a center body, the cowl having a cowl lip and the center body having an apex, a first compression surface downstream of the apex, and a second compression surface downstream of first compression surface; positioning the center body with respect to the cowl such that: the center body is coaxial with the cowl, a protruding portion of the center body extends upstream of the cowl lip, and the second compression surface is spaced apart from the cowl lip such that the second compression surface and the cowl lip define an inlet, wherein the protruding portion of the center body is configured to displace a portion of a column of air disposed upstream of the center body and longitudinally aligned therewith when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed, the column of air having a periphery defined by a leading edge of the cowl, the portion of the column of air being displaced out of the path of the inlet by the protruding portion of the center body such that a remaining sub-portion of the column of air at an upstream boundary of a terminal shock of the inlet is not greater than an amount of air that can be consumed by the supersonic jet engine when the supersonic jet engine consumes air at the first predetermined mass flow rate while the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed. 16. The method of claim 15, wherein providing the center body comprises providing the center body having a second compression surface configured to cause isentropic compression. 17. The method of claim 15, wherein providing the center body comprises providing the center body having a second compression surface configured to cause relaxed isentropic compression. 18. The method of claim 15, wherein providing the center body comprises providing the center body having an expansion surface disposed between the first compression surface and the second compression surface. 19. The method of claim 15, further comprising providing a bypass splitter and positioning the bypass splitter between the cowl and the center body to form a bypass configured to receive air at a second predetermined mass flow rate when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed, and wherein the remaining sub-portion of the column of air approaching and entering the inlet is not greater than the first predetermined mass flow rate and the second predetermined mass flow rate combined when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed. 20. The method of claim 19, wherein providing the center body comprises providing the center body having an expansion surface disposed between the first compression surface and the second compression surface and wherein the second compression surface is configured to cause relaxed isentropic compression.
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이 특허에 인용된 특허 (2)
Sorensen Norman E. (Saratoga CA) Latham Eldon A. (Sunnyvale CA), Jet engine air intake system.
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