Trailing edge core compartment vent for an aircraft engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-033/04
B64D-027/12
B64D-029/00
F02K-001/82
F02K-003/04
F01D-025/26
F02K-001/38
F02C-007/18
출원번호
US-0870401
(2015-09-30)
등록번호
US-10040560
(2018-08-07)
발명자
/ 주소
Willie, Robert H.
Tretow, Paul R.
Cerra, David F.
출원인 / 주소
THE BOEING COMPANY
대리인 / 주소
MH2 Technology Law Group LLP
인용정보
피인용 횟수 :
0인용 특허 :
9
초록▼
A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl
A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl terminus to form a core compartment vent nozzle. The core compartment vent nozzle exhausts air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall.
대표청구항▼
1. A turbine engine nozzle, comprising: a primary outer wall directly coupled to a trailing end of an engine core and extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, the primary outer wall forming a core nozzle; anda single engine core cowl extendin
1. A turbine engine nozzle, comprising: a primary outer wall directly coupled to a trailing end of an engine core and extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, the primary outer wall forming a core nozzle; anda single engine core cowl extending from the engine core area to an annular cowl terminus, the single engine core cowl forming a core compartment vent nozzle,wherein: the core compartment vent nozzle is configured to exhaust air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall,the annular cowl terminus is in substantially planar alignment with the annular wall terminus, andat the trailing edge between the single engine core cowl and the primary outer wall, the primary outer wall is substantially parallel to the single engine core cowl. 2. The turbine engine nozzle of claim 1, wherein the core compartment vent nozzle comprises an annulus between the annular cowl terminus of the single engine core cowl and annular wall terminus of the primary outer wall. 3. The turbine engine nozzle of claim 1, wherein the core compartment vent nozzle comprises a circular annulus around the complete circumference of the engine tail cone. 4. The turbine engine nozzle of claim 3, wherein the core compartment vent nozzle is configured to vent the air around the entire circumference of the engine tail cone into a trailing edge between a fan air flow flowing outside of the single engine core cowl and a core air flow flowing between the primary outer wall and the engine tail cone. 5. The turbine engine nozzle of claim 1, wherein the single core cowl comprises only one core cowl and the turbine engine nozzle lacks any other core cowls. 6. The turbine engine nozzle of claim 1, wherein the turbine engine nozzle lacks any batwing ramp configured to transition the air from the single core cowl. 7. An aircraft engine, comprising a ducted fan comprising a fan airflow exit configured to exhaust a fan air flow;a core gas turbine engine comprising: a core nozzle configured to exhaust a core air flow from the turbine engine core,a core compartment vent nozzle configured to exhaust a core compartment vent air flow from a core compartment; andan engine tail cone,wherein the core compartment vent nozzle is configured to exhaust a compartment vent air flow at a trailing edge between the fan air flow and the core air flow, andwherein the turbine engine comprises: a primary outer wall directly coupled to a trailing end of an engine core, and extending from an engine core area to an annular wall terminus that surrounds the engine tail cone, the primary outer wall forming the core nozzle,a single engine core cowl extending the engine core area to an annular cowl terminus, the single engine core cowl forming a core compartment vent nozzle,the annular cowl terminus is in substantially planar alignment with the annular wall terminus, andat the trailing edge between the single engine core cowl and the primary outer wall, the primary outer wall is substantially parallel to the single engine core cowl. 8. The aircraft engine of claim 7, wherein the core compartment vent nozzle comprises an annular gap between the single engine core cowl and the primary outer wall. 9. The aircraft engine of claim 7, further comprising: an engine cover at least partially enclosing the ducted fan and the turbine engine core. 10. An aircraft comprising: an aircraft body comprising a fuselage and at least one wing; andat least one aircraft engine, the at least one aircraft engine comprising: a ducted fan comprising a fan airflow exit for exhausting a fan air flow, anda turbine engine core comprising: a core nozzle configured to exhaust a core air flow from the turbine engine core, anda core compartment vent nozzle configured to exhaust a core compartment vent air flow from a core compartment; andan engine tail cone,wherein the core compartment vent nozzle exhausts core compartment vent air flow through a trailing edge between the fan air flow and the core air flow, andwherein the turbine engine core comprises: a primary outer wall directly coupled to a trailing end of an engine core, and extending from an engine core area to an annular wall terminus that surrounds the engine tail cone, the primary outer wall forming the core nozzlea single engine core cowl the engine core area to an annular cowl terminus, the single engine core cowl forming the core compartment vent nozzle,the annular cowl terminus is in substantially planar alignment with the annular wall terminus, andat the trailing edge between the single engine core cowl and the primary outer wall, the primary outer wall is substantially parallel to the single engine core cowl. 11. The aircraft of claim 10, wherein the core compartment vent nozzle comprises an annular gap between the single engine core cowl and the primary outer wall. 12. The aircraft of claim 10, further comprising: an engine cover at least partially enclosing the ducted fan and the turbine engine core. 13. The aircraft of claim 10, wherein the at least one aircraft engine is coupled to the at least one wing. 14. An aircraft engine, comprising: a ducted fan comprising a fan airflow exit configured to exhaust fan air; anda turbine engine core comprising: an engine core;a tail cone at a trailing end of the engine core;a primary outer wall around the tail cone, the primary outer wall directly coupling to a trailing edge of the core and extending from an engine core area to an annular wall terminus and forming a core nozzle configured to exhaust core air; andan engine core cowl around the primary outer wall, the engine cowl extending from the engine core area to an annular cowl terminus forming a core compartment vent nozzle configured to exhaust core vent air,wherein: the core compartment vent nozzle comprises a circular annulus around the complete circumference of the tail cone,the core compartment vent nozzle is configured to exhaust the core vent air around the entire circumference of the tail cone into the trailing edge, between the engine core cowl and the primary outer wall,the primary outer wall is parallel to the engine core cowl at the trailing edge,the annular cowl terminus is in planar alignment with the annular wall terminus around the trailing edge,at the trailing edge between the single engine core cowl and the primary outer wall, the primary outer wall is substantially parallel to the single engine core cowl, andthe turbine engine core lacks any batwing ramp configured to transition the air from the core cowl.
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이 특허에 인용된 특허 (9)
Spring Samuel D. ; Carita Robert J. ; Stocking Herbert A., Bay cooled turbine casing.
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