[특허]Tip turbine single plane mount

[미국특허] Tip turbine single plane mount 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/20 F02K-003/068 B64D-027/26 F02C-003/073
출원번호	US-0720470 (2004-12-04)
등록번호	US-9109537 (2015-08-18)
국제출원번호	PCT/US2004/040077 (2004-12-04)
§371/§102 date	20070530 (20070530)
국제공개번호	WO2006/062497 (2006-06-15)
발명자 / 주소	Suciu, Gabriel L. Norris, James W. Merry, Brian
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 1 인용 특허 : 73

초록 ▼

A tip turbine engine assembly (8) includes a fan (32) rotatable in a fan plane (22) about an engine centerline (112). The fan (32) includes a fan blade (34) that defines a core airflow passage therethrough. An engine case (10) surrounds and supports the fan and engine. A plurality of engine mounts (20) for mounting the engine to an aircraft are positioned circumferentially about the outside of the engine case in a single mounting plane (22) that is perpendicular to the engine centerline.

대표청구항 ▼

1. A tip turbine engine assembly comprising: a fan rotatable in a fan plane about an engine centerline, said fan including a fan blade defining a core airflow passage there through;a turbine rotatable about said engine centerline aft of said fan;an engine case disposed about said engine centerline; anda plurality of engine mounts attached to said engine case substantially in a single mounting plane that is substantially perpendicular to said engine centerline, wherein said single mounting plane is located aft of said turbine, forward of said fan plane, or coplanar with said turbine and said fan plane. 2. The tip turbine engine assembly as recited in claim 1, wherein said plurality of engine mounts provides an exclusive support attachment on the engine case for attachment to an aircraft. 3. The tip turbine engine assembly as recited in claim 1, wherein said single mounting plane is axially aft of said turbine relative to the engine centerline. 4. The tip turbine engine assembly as recited in claim 1, wherein said single mounting plane is axially forward of said fan relative to the engine centerline. 5. The tip turbine engine assembly as recited in claim 1, wherein said single mounting plane is coplanar with said fan plane and said turbine. 6. The tip turbine engine assembly as recited in claim 1, wherein said plurality of engine mounts includes two engine mounts. 7. The tip turbine engine assembly as recited in claim 1, wherein a combustor is located radially outward of the fan blade and receives core airflow from the fan blade. 8. The tip turbine engine assembly as recited in claim 7, wherein the combustor is axially forward of the turbine. 9. The tip turbine engine as recited in claim 1, wherein the fan blade includes a diffuser section at an outer radial end relative to the engine centerline, wherein the diffuser turns the core airflow in an axial forward direction into a combustor. 10. The tip turbine engine assembly as recited in claim 1, wherein an axial compressor is axially forward of the fan blade and providing air to an inducer of the core airflow passage. 11. The tip turbine engine as recited in claim 1, wherein the core airflow passage turns airflow from an axial direction towards a combustor. 12. A tip turbine engine assembly comprising: a fan rotatable in a fan plane about an engine centerline, said fan including a fan blade defining a core airflow passage there through;a turbine rotatable about said engine centerline aft of said fan;an engine case disposed about said engine centerline;a plurality of first engine mounts attached to said engine case substantially in a first mounting plane that is substantially perpendicular to said engine centerline, wherein said first mounting plane is located aft of said turbine, forward of said fan plane, or coplanar with said turbine and said fan plane; anda plurality of second engine mounts attached to said engine case substantially in a second mounting plane. 13. The tip turbine engine assembly as recited in claim 12, wherein said first mounting plane is substantially parallel to said second mounting plane. 14. The tip turbine engine assembly as recited in claim 12, wherein said first mounting plane is axially aft of said turbine relative to the engine centerline. 15. The tip turbine engine assembly as recited in claim 12, wherein said first mounting plane is axially forward of said fan plane relative to the engine centerline. 16. The tip turbine engine assembly as recited in claim 12, wherein said first mounting plane is coplanar with said fan plane and said turbine. 17. The tip turbine engine assembly as recited in claim 12, wherein a combustor is located radially outward of the fan blade and receives core airflow from the fan blade. 18. A tip turbine engine assembly comprising: a fan rotatable in a fan plane about an engine centerline, said fan including a fan blade defining a core airflow passage there through;a turbine rotatable about said engine centerline aft of said fan;an engine case disposed about said engine centerline;a plurality of first engine mounts attached to said engine case substantially in a single mounting plane that is substantially perpendicular to said engine centerline, wherein said single mounting plane is located aft of said turbine, forward of said fan plane, or coplanar with said turbine and said fan plane; anda second engine mount attached to said engine case remote from said single mounting plane. 19. The tip turbine engine assembly as recited in claim 18, wherein all of said plurality of first engine mounts are substantially inside said single mounting plane. 20. The tip turbine engine assembly as recited in claim 18, wherein said single mounting plane is axially aft of said fan relative to the engine centerline. 21. The tip turbine engine assembly as recited in claim 18, wherein said single mounting plane and said second engine mount are axially aft of said fan relative to the engine centerline. 22. The tip turbine engine assembly as recited in claim 18, wherein said single mounting plane and said second engine mount are axially forward of said fan relative to the engine centerline. 23. The tip turbine engine assembly as recited in claim 18, wherein a combustor is located radially outward of the fan blade and receives core airflow from the fan blade.

이 특허에 인용된 특허 (73) 인용/피인용 타임라인 분석

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이 특허를 인용한 특허 (1) 인용/피인용 타임라인 분석

Eastwood, Jonathan J.; Hyland, Dave J.; Dale, Timothy, Outer diffuser case for a gas turbine engine.
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[미국특허] Tip turbine single plane mount 원문보기

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[미국특허] Tip turbine single plane mount 원문보기

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