Stiffener for low pressure compressor for an aircraft engine
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0172804
(2005-07-05)
|
등록번호 |
US-7634916
(2010-01-08)
|
우선권정보 |
FR-04 51437(2004-07-05) |
발명자
/ 주소 |
- Mace, Jerome
- Lejars, Claude
- Maillard, Pierre Yves
- Buffenoir, Francois
- Niclot, Thierry
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
|
인용정보 |
피인용 횟수 :
7 인용 특허 :
5 |
초록
▼
Unbalanced mass effects can occur at the low pressure compressor (5) of an aircraft engine. Stiffeners (20) are proposed to increase the stiffness of the assembly and therefore reduce possible cracks due to accidental unbalanced masses, one end (22) of the stiffener can be fixed to the engine casing
Unbalanced mass effects can occur at the low pressure compressor (5) of an aircraft engine. Stiffeners (20) are proposed to increase the stiffness of the assembly and therefore reduce possible cracks due to accidental unbalanced masses, one end (22) of the stiffener can be fixed to the engine casing (7) at the structural arm (10), and the other end (32) can be fixed to the compressor (5), preferably at the upstream face of the third guide vane (RD3). Advantageously, the stiffeners (20) are made of two parts fixed to each other; their manufacturing is optimized to limit the additional weight due to their presence.
대표청구항
▼
The invention claimed is: 1. A stiffener to stiffen a low pressure compressor part of an aircraft engine, said stiffener comprising: a four-sided element having two pairs of opposite sides, a first pair having straight sides of equal length and a second pair having curved sides of unequal length wi
The invention claimed is: 1. A stiffener to stiffen a low pressure compressor part of an aircraft engine, said stiffener comprising: a four-sided element having two pairs of opposite sides, a first pair having straight sides of equal length and a second pair having curved sides of unequal length with a smaller side and a larger side, the smaller side comprising first attachment means for connecting the stiffener to a casing of said aircraft engine, the larger side comprising second attachment means for connecting the stiffener to a low pressure compressor of said aircraft engine, the first and second sides being curved about a longitudinal axis of said aircraft engine, wherein the four-sided element is made of two independent parts configured to be fixed together, a first part comprising the smaller side, and a second part comprising the larger side. 2. A stiffener according to claim 1, wherein said four-sided element is made of aluminum. 3. A stiffener according to claim 1, wherein a distance along a normal separating the smaller side and the larger side is of the order of 265 mm. 4. A stiffener according to claim 1, wherein the smaller side has a length of the order of 255 mm and the larger side has a length of the order of 435 mm. 5. A stiffener according to claim 1, wherein the first and second attachment means are holes. 6. A stiffener according to claim 5, wherein the first attachment means are composed of six holes and the second attachment means are composed of seven holes. 7. A stiffener according to claim 1, wherein the second part has an approximately L shaped cross-section. 8. A stiffener according to claim 7, wherein a distance separating the smaller side from side of the first part opposite the smaller side along a normal is of the order of 240 mm. 9. A stiffener according to claim 1, wherein each of the first and second parts comprises fixing means to fix the two parts together on a side opposite the smaller and larger sides respectively. 10. A stiffener according to claim 9, wherein the fixing means are composed of holes and screws to fix the two parts through the said holes. 11. A stiffener according to claim 1, wherein said smaller side is in a range from 240 mm to 350 mm, and said larger side is in a range from 350 mm to 500 mm. 12. An aircraft engine comprising a casing, a low pressure compressor and a plurality of identical stiffeners connecting said casing to said low pressure compressor, each of said stiffeners comprising: a four-sided element having two pairs of opposite sides, a first pair having straight sides of equal length and a second pair having curved sides of unequal length with a smaller side and a larger side, the smaller side comprising first attachment means for connecting the stiffener to a casing of said aircraft engine, the larger side comprising second attachment means for connecting the stiffener to a low pressure compressor of said aircraft engine, the first and second sides being curved about a longitudinal axis of said aircraft engine. 13. An aircraft engine according to claim 12, wherein said stiffeners are uniformly distributed around said longitudinal axis of said aircraft engine. 14. An aircraft engine according to claim 13, wherein said stiffeners are a total of five in number. 15. An aircraft engine according to claim 14, wherein each of said stiffeners extend over an angle of about 30° around said longitudinal axis of said aircraft engine.
이 특허에 인용된 특허 (5)
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Boeck Alexander,DEX, Casing construction on a gas turbine jet engine.
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Jensen Daniel T. ; Balzer Ronald L., Flow control apparatus for gas turbine engine installation pressure relief doors.
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Romani Giuseppe,CAX, Integrated fan / low pressure compressor rotor for gas turbine engine.
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Ernest Boratgis ; James B. Coffin, Turbine engine bearing support.
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Kulak Andrew C. (Hartford CT) White Richard T. (West Hartford CT), Turbofan containment structure.
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Eleftheriou, Andreas; Menheere, David; Liu, Quantai, Fabricated intermediate case with engine mounts.
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Merry, Brian D.; Suciu, Gabriel L.; Hasel, Karl L., Gas turbine engine shaft bearing configuration.
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