IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0496832
(2009-07-02)
|
등록번호 |
US-8418953
(2013-04-16)
|
우선권정보 |
GB-0813483.5 (2008-07-24) |
발명자
/ 주소 |
- Smith, Angus Roy
- Arzoglou, Dimitris
|
출원인 / 주소 |
|
대리인 / 주소 |
McCormick, Paulding & Huber LLP
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
2 |
초록
▼
A nacelle for a gas turbine engine has an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, an intake lip and a diffuser. The diffuser has a main diffuser section and an optional shorter straight wall diffuser section. The main diffuser se
A nacelle for a gas turbine engine has an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, an intake lip and a diffuser. The diffuser has a main diffuser section and an optional shorter straight wall diffuser section. The main diffuser section is bounded by an inner wall of the nacelle, the inner wall curving in the airflow direction of the engine. On each longitudinal section containing the engine axis, at the downstream end of the main diffuser section the inner wall has a non zero curvature. Thus each circumferential position on the inner wall at the downstream end of the main diffuser section has a curvature defined by a respective radius of curvature. However, one or more of the radii of curvature differ from the others of the radii of curvature.
대표청구항
▼
1. A nacelle for a gas turbine engine, the nacelle comprising: an intake at the upstream end of the nacelle having, in flow series, an intake lip and a diffuser;wherein the diffuser has a main diffuser section that is bounded by an inner wall of the nacelle, the inner wall curving in an airflow dire
1. A nacelle for a gas turbine engine, the nacelle comprising: an intake at the upstream end of the nacelle having, in flow series, an intake lip and a diffuser;wherein the diffuser has a main diffuser section that is bounded by an inner wall of the nacelle, the inner wall curving in an airflow direction of the engine and, on each longitudinal section containing the longitudinal axis of the nacelle, at the downstream end of the main diffuser section the inner wall having a curvature, whereby each circumferential position on the inner wall at the downstream end of the main diffuser section has the curvature defined by a respective radius of curvature, and one or more of said radii of curvature differs from the others of said radii of curvature, wherein around the circumference of the inner wall, a ratio of the largest radius of curvature to the smallest radius of curvature is at least 2; andan exhaust at a downstream end of the nacelle. 2. A nacelle according to claim 1, wherein said radii of curvature vary smoothly around the circumference of the inner wall. 3. A nacelle according to claim 1, wherein the diffuser further comprises a straight wall section upstream of the main diffuser section. 4. A gas turbine engine comprising: a nacelle having an intake at the upstream end of the nacelle having, in flow series, an intake lip and a diffuser; wherein the diffuser has a main diffuser section that is bounded by an inner wall of the nacelle, the inner wall curving in an airflow direction of the engine and, on each longitudinal section containing the longitudinal axis of the nacelle, at the downstream end of the main diffuser section the inner wall having a curvature, whereby each circumferential position on the inner wall at the downstream end of the main diffuser section has the curvature defined by a respective radius of curvature; and where one or more of said radii of curvature differs from the others of said radii of curvature, wherein around the circumference of the inner wall, a ratio of the largest radius of curvature to the smallest radius of curvature is at least 2, andan exhaust at a downstream end of the nacelle. 5. A method of designing a nacelle for a gas turbine engine comprising the steps of: defining an initial geometry for a nacelle, the initial geometry providing an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle, wherein the intake has, in flow series, an intake lip and a diffuser, the diffuser having a main diffuser section that is bounded by an inner wall of the nacelle, the inner wall curving in an airflow direction of the engine and, on each longitudinal section containing the longitudinal axis of the nacelle, at the downstream end of the main diffuser section the inner wall having a curvature, whereby each position around the circumference of the inner wall at the downstream end of the main diffuser section has the curvature defined by a respective radius of curvature; altering one or more of said radii of curvature; andadjusting the inner wall at regions neighbouring each altered radius of curvature to smoothly blend the inner wall at each altered radius of curvature to unadjusted parts of the inner wall further removed from the altered radius of curvature to obtain an altered geometry for the nacelle,wherein, in the altered geometry, around the circumference of the inner wall, the ratio of the largest radius of curvature to the smallest radius of curvature is selected to be at least 2. 6. A method of designing a nacelle according to claim 5, wherein the defining, altering and obtaining steps are performed on a computer system. 7. A method of designing a nacelle according to claim 5, wherein in the obtaining step the inner wall at regions neighbouring each altered radius of curvature is also adjusted to smoothly vary the radii of curvature around said circumference. 8. A method of designing a nacelle according to claim 5, wherein in the initial geometry all said radii of curvature are identical. 9. A nacelle for a gas turbine engine made in accordance with a method comprising the steps of: defining an initial geometry for a nacelle, the initial geometry providing an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle, wherein the intake has, in flow series, an intake lip and a diffuser, the diffuser having a main diffuser section that is bounded by an inner wall of the nacelle, the inner wall curving in an airflow direction of the engine and, on each longitudinal section containing the longitudinal axis of the nacelle, at the downstream end of the main diffuser section the inner wall having a curvature, whereby each position around the circumference of the inner wall at the downstream end of the main diffuser section has the curvature defined by a respective radius of curvature; altering one or more of said radii of curvature; andadjusting the inner wall at regions neighbouring each altered radius of curvature to smoothly blend the inner wall at each altered radius of curvature to unadjusted parts of the inner wall further removed from the altered radius of curvature to obtain an altered geometry for the nacelle,wherein, in the altered geometry, around the circumference of the inner wall, the ratio of the largest radius of curvature to the smallest radius of curvature is selected to be at least 2.
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