Stiffener for low pressure compressor for an aircraft engine
View Patent ↗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 (RD 3 ). 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.
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.