IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0195264
(2011-08-01)
|
등록번호 |
US-8443585
(2013-05-21)
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발명자
/ 주소 |
|
출원인 / 주소 |
- United Technologies Corporation
|
대리인 / 주소 |
Carlson, Gaskey & Olds, P.C.
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인용정보 |
피인용 횟수 :
1 인용 특허 :
17 |
초록
▼
A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap between the first nozzle section a
A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap between the first nozzle section and the second nozzle section. A movable door between the first nozzle section and the second nozzle section selectively opens or closes the gap.
대표청구항
▼
1. A gas turbine engine system, comprising: a first nozzle section;a second nozzle section, wherein the first nozzle section and the second nozzle section at least partially define a gas turbine engine bypass passage, wherein the second nozzle section is axially translatable relative to the first no
1. A gas turbine engine system, comprising: a first nozzle section;a second nozzle section, wherein the first nozzle section and the second nozzle section at least partially define a gas turbine engine bypass passage, wherein the second nozzle section is axially translatable relative to the first nozzle section such that there is a gap between the first nozzle section and the second nozzle section when the second nozzle section is moved from a first position to a second position; anda moveable door at least partially between the first nozzle section and the second nozzle section for selectively opening and closing the gap, wherein the moveable door includes a thrust reverse cascade between a radially inner surface of the moveable door and a radially outer surface of the moveable door relative to an engine centerline, the thrust reverse cascade including tracks to guide the moveable door during axial translation. 2. The gas turbine engine system as recited in claim 1, wherein the gas turbine engine bypass passage includes a radially inner surface and a radially outer surface relative to an engine centerline, and the first nozzle section and the second nozzle section form at least a portion of the radially outer surface. 3. The gas turbine engine system as recited in claim 2, wherein the movable door is located radially outwards of the gas turbine engine bypass passage relative to the engine centerline axis. 4. The gas turbine engine system as recited in claim 1, including a thrust reverse blocker door connected to the moveable door via a linkage. 5. The gas turbine engine as recited in claim 4, wherein the thrust reverse blocker door rotates axially forward in response to movement of the moveable door. 6. The gas turbine engine system as recited in claim 1, wherein thrust reverse cascade includes a plurality of vents. 7. The gas turbine engine system as recited in claim 6, wherein the plurality of vents change the direction of airflow in the gas turbine engine bypass passage. 8. The gas turbine engine system as recited in claim 1, further comprising a seal between the first nozzle section and the second nozzle section in the first position. 9. The gas turbine engine system as recited in claim 1, wherein the moveable door includes an axially forward side attached to the radially inner side of the moveable door and the radially outer side of the moveable door, wherein the axially forward side is connected to an actuator via a linkage. 10. The gas turbine engine system of claim 1, wherein the combustion section and the turbine section define a core airflow passage, wherein the gas turbine fan bypass passage is radially outward of the core airflow passage. 11. The gas turbine engine of claim 10, wherein the core airflow is discharged from the core airflow passage between an inner cowl and a tail cone. 12. The gas turbine engine system of claim 1, wherein the gas turbine fan bypass passage is in fluid communication with the fan. 13. The gas turbine engine system of claim 1, wherein the gas turbine bypass passage bypasses a compressor section, a combustor section, and a turbine section. 14. A gas turbine engine system, comprising: a fan;a combustion section downstream of the fan;a turbine section downstream of the combustion section;a fan bypass passage downstream from the fan;a nozzle defining at least a portion of the fan bypass passage and having a first nozzle section and a second nozzle section axially translatable relative to the first nozzle section such that there is a gap between the first nozzle section and the second nozzle section when the second nozzle section is moved from a first position to a second position; anda moveable door at least partially between the first nozzle section and the second nozzle section for selectively opening and closing the gap, wherein an actuator is attached to the moveable door to move the moveable door independent of the second nozzle section. 15. The gas turbine engine system of claim 14, wherein the actuator is connected to the moveable door and the second nozzle section using a linkage with a plurality of telescopic links. 16. The gas turbine engine system of claim 15, wherein the moveable door includes a thrust reverse cascade between a radially inner surface of the moveable door and a radially outer surface of the moveable door relative to an engine centerline, the thrust reverse cascade including tracks guiding the moveable door during axial translation. 17. The gas turbine engine system as recited in claim 14, further including a thrust reverse blocker door pivotably attached to an inner cowl, wherein the inner cowl defines a radially inner side of the fan bypass passage. 18. The gas turbine engine system as recited in claim 17, wherein the thrust reverse blocker door is attached to the inner cowl on a first end and to a linkage on a second end, wherein the linkage is attached to the moveable door, wherein the thrust reverse blocker door moves in response to movement of the moveable door. 19. The gas turbine engine as recited in claim 17, wherein the thrust reverse blocker door moves in the same axial direction as the moveable door when moving from an closed position to an open position. 20. The gas turbine engine system of claim 17, wherein the thrust reverse blocker door includes a free end and a fixed end. 21. The gas turbine engine system of claim 14, wherein the combustion section and the turbine section define a core airflow passage, wherein the fan bypass passage is radially outward of the core airflow passage. 22. A gas turbine engine system, comprising: a first nozzle section;a second nozzle section, wherein the first nozzle section and the second nozzle section at least partially define a gas turbine engine bypass passage, wherein the second nozzle section is axially translatable relative to the first nozzle section such that there is a gap between the first nozzle section and the second nozzle section when the second nozzle section is moved from a first position to a second position; anda moveable door at least partially between the first nozzle section and the second nozzle section for selectively opening and closing the gap, wherein the moveable door is independently moveable relative to the second nozzle section, wherein the moveable door includes a thrust reverse cascade between a radially inner surface of the moveable door and a radially outer surface of the moveable door relative to an engine centerline, the thrust reverse cascade including tracks guiding the moveable door during axial translation. 23. The gas turbine engine system as recited in claim 22, wherein a first actuator axially translates the second nozzle section and a second actuator axially translates the moveable door. 24. The gas turbine engine system as recited in claim 23, wherein the first actuator axially translates the second nozzle section in an axial direction opposite the axial translation of the second nozzle section during thrust reversing. 25. The gas turbine engine system as recited in claim 24, further including a thrust reverse blocker door for thrust reversing. 26. A gas turbine engine system comprising: a fan disposed about an engine centerline;a fan bypass passage downstream from the fan;a nozzle defining at least a portion of the fan bypass passage and having a first nozzle section and a second nozzle section axially translatable relative to the first nozzle section such that there is a gap between the first nozzle section and the second nozzle section when the second nozzle section is moved from a first position to a second position; anda moveable door at least partially between the first nozzle section and the second nozzle section for selectively opening and closing the gap, wherein an actuator is attached to the moveable door to move the moveable door independent of the second nozzle section;a gear train having a reduction ratio of greater than 2.5:1, wherein the gear train drives the fan;a low pressure compressor disposed about the engine centerline, wherein the fan has a diameter greater than a diameter of the low pressure compressor, the gas turbine engine system having a bypass ratio greater than 10:1;a high pressure compressor;a combustion section;a high pressure turbine that drives the high pressure compressor; anda low pressure turbine having a pressure ratio greater than 5:1, wherein the low pressure turbine drives the low pressure compressor and the gear train. 27. The gas turbine engine system of claim 26, wherein the fan draws air flow into the fan bypass passage, air flow exits the fan bypass passage at an exhaust having a variable cross-sectional area, wherein thrust generated by the gas turbine engine system varies relative to the variable cross-sectional area of said exhaust. 28. The gas turbine engine system of claim 26, wherein the fan draws air flow into the fan bypass passage, air flow exits the fan bypass passage at an exhaust having a variable cross-sectional area, wherein the pressure ratio across the fan varies relative to the variable cross-sectional area of said exhaust.
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