IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0440623
(2006-10-12)
|
등록번호 |
US-8276364
(2012-10-02)
|
국제출원번호 |
PCT/US2006/039807
(2006-10-12)
|
§371/§102 date |
20091229
(20091229)
|
국제공개번호 |
WO2008/045057
(2008-04-17)
|
발명자
/ 주소 |
|
출원인 / 주소 |
- United Technologies Corporation
|
대리인 / 주소 |
Carlson, Gaskey & Olds, P.C.
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
2 |
초록
A variable fan nozzle for use in a gas turbine engine includes a nozzle section, such as an inflatable bladder, associated with a fan bypass passage for conveying a bypass airflow. The nozzle section has an internal fluid pressure that is selectively variable to influence the bypass airflow.
대표청구항
▼
1. A variable fan nozzle for use in a gas turbine engine, comprising: a nozzle section associated with a fan bypass passage for conveying a bypass airflow, the nozzle section having an inflatable bladder that is selectively variable to influence the bypass airflow; anda first flap abutting the infla
1. A variable fan nozzle for use in a gas turbine engine, comprising: a nozzle section associated with a fan bypass passage for conveying a bypass airflow, the nozzle section having an inflatable bladder that is selectively variable to influence the bypass airflow; anda first flap abutting the inflatable bladder and a second flap abutting the inflatable bladder, wherein the second flap is radially inwards of the first flap, and wherein the second flap moves between a plurality of positions in response to changes in the inflatable bladder, the first flap and the second flap abutting the inflatable bladder at each of the plurality of positions. 2. The variable fan nozzle recited in claim 1, wherein the inflatable bladder has flexible walls that define a volumetric size that changes depending on a contained internal fluid pressure of the inflatable bladder. 3. The variable fan nozzle of claim 2, wherein the second flap moves radially outwards in response to a decrease in the volumetric size. 4. The variable fan nozzle of claim 2, wherein the second flap moves radially inwards in response to an increase in the volumetric size. 5. The variable fan nozzle recited in claim 1, further comprising a pressurized fluid source connected to the inflatable bladder for selectively providing pressurized fluid to change a contained internal fluid pressure of the inflatable bladder. 6. The variable fan nozzle recited in claim 1, further comprising at least one sensor near the nozzle section that produces a signal representative of a contained internal fluid pressure of the inflatable bladder. 7. The variable fan nozzle recited in claim 1, wherein the inflatable bladder has flexible walls such that the first flap and the second flap move between the Plurality of positions in response to movement of the flexible walls. 8. The variable fan nozzle recited in claim 7, wherein the inflatable bladder comprises a plurality of inflatable bladders connected with a supply manifold and a pressurized fluid source, the supply manifold having at least one bleed valve that releases pressurized fluid from the plurality of inflatable bladders in response to a contained internal fluid pressure of the plurality of inflatable bladders exceeding a threshold pressure. 9. The variable fan nozzle of claim 1, wherein the first flap is a fixed flap and the second flap defines an outer radial side of the fan bypass passage. 10. The variable fan nozzle of claim 1, wherein an increase in a contained internal fluid pressure of the inflatable bladder is in response to a take-off flight condition. 11. The variable fan nozzle of claim 1, wherein at least one sensor adjacent the second flap produces a signal representative of a relative position of the second flap. 12. The variable fan nozzle of claim 1, wherein the first flap moves between a plurality of positions. 13. A gas turbine engine system comprising: a fan;a nacelle arranged about the fan having a radially innermost wall;a gas turbine engine core having a compressor and a turbine at least partially within the nacelle;a fan bypass passage downstream of the fan between the nacelle and the gas turbine engine, for conveying a bypass airflow from the fan;a nozzle associated with a fan bypass passage, the nozzle comprising:a first flap;a second flap that is radially inwards of the first flap;at least one bladder located between the first flap and the second flap, the at least one bladder having flexible walls and a contained internal fluid pressure that is selectively variable to influence the bypass airflow, wherein the second flap moves radially inwards of the radially innermost wall into the fan bypass passage in a first position in response to an increase in the contained internal fluid pressure; anda controller that selectively varies the contained internal fluid pressure. 14. The gas turbine engine system recited in claim 13, wherein the first flap and the second flap are nominally radially equidistant from an engine centerline axis, wherein the at least one bladder is located adjacent the two flaps. 15. The gas turbine engine system recited in claim 13, wherein at east one flap is pivotally connected to the nacelle. 16. The gas turbine engine system recited in claim 13, further comprising a pressurized fluid source that selectively provides pressurized fluid to change the contained internal fluid pressure in response to a signal from the controller. 17. The gas turbine engine system recited in claim 13, further comprising at least one sensor near the nozzle that produces a signal representative of the contained internal fluid pressure, wherein the controller selectively varies the contained internal fluid pressure in response to the signal. 18. The gas turbine engine system recited in claim 17, wherein the at least one sensor is operative to produce a fault signal in response to a gradual decrease of the contained internal fluid pressure. 19. The gas turbine engine of claim 17 wherein the controller generates a fault signal in response to having to inflate the bladder a predetermined number of times over a predetermined time period. 20. The gas turbine engine system of claim 13, wherein the second flap defines an outer radial side of the fan bypass passage. 21. The gas turbine engine system of claim 13, wherein a cross sectional area is defined between the second flap and the gas turbine engine core. 22. The gas turbine engine system of claim 21, wherein the cross sectional area decreases in response to an increase in the contained internal fluid pressure. 23. The gas turbine engine system of claim 21, wherein the cross sectional area decreases as the second flap moves radially inwards and increases as the second flap moves radially outwards. 24. The gas turbine engine of claim 13, wherein the bladder is disposed outside of the fan bypass passage. 25. A method for controlling a bypass airflow through a fan bypass passage in a gas turbine engine, comprising the steps of: selectively varying a contained internal fluid pressure within a flexible bladder of a nozzle section adjacent the fan bypass passage to thereby move at least a first flap or a second flap, located radially inwards of the first flap, that the flexible bladder is between and influence the bypass airflow, wherein the first flap and the second flap abut the inflatable bladder at each of a plurality of positions: andcommunicating a signal representing the distance between an inner cowl and the second flap. 26. The method recited in claim 25, including increasing the contained internal fluid pressure to expand the nozzle section into the fan bypass passage to restrict the bypass airflow through the fan bypass passage. 27. The method recited in claim 25, including decreasing the contained internal fluid pressure to retract the nozzle section out of the fan bypass passage to augment the bypass airflow through the fan bypass passage. 28. The method recited in claim 25, including selectively varying the contained internal fluid pressure within a bladder of the nozzle section to move at least one flap adjacent the bladder. 29. The method recited in claim 25, wherein both the first flap and the second flap are moveable. 30. A variable fan nozzle for use in a gas turbine engine comprising: a nozzle section associated with a fan bypass passage for conveying a bypass airflow, the nozzle section having a contained internal fluid pressure that is selectively variable to influence the bypass airflow;at least one flap adjacent the nozzle section that moves between a plurality of positions in response to changes in the contained internal fluid pressure, wherein the at least one flap moves into the fan bypass passage in a first position in response to an increase in the contained internal fluid pressure; andat least one sensor near the at least one flap that produces a signal representative of a relative position of the at least one flap, wherein the sensor is on the at least one flap.
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