Compressor with centripetal air takeoff
View Patent ↗A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between the pipe and the inner collar.
1. A compressor with centripetal air offtake, which includes several radially oriented pipes, regularly distributed circumferentially, said pipes being installed between two coaxial collars of a rotor of said compressor, respectively an outer collar and an inner collar, a space outside said outer collar communicating with an air stream of said compressor, wherein one end of each pipe is fitted in a hole in said outer collar, wherein each pipe is fitted in a hole in said inner collar and wherein a locking mechanism, defined between such a pipe and said inner collar, comprises:
a flange fixed to each pipe, provided with a flat section;
an annular slot with lateral opening, defined on the internal face of said inner collar and a removable annular limit stop projecting from said internal face, parallel to said annular slot;
said flange being fitted in said slot and its flat section being opposite said annular limit stop.
2. The compressor as claimed in claim 1 , wherein said annular limit stop is a retaining ring mounted in a groove in said inner collar.
3. The compressor as claimed in claim 2 , wherein said annular slot with lateral opening is defined in an annular rib projecting from the internal face of said inner collar.
4. The compressor as claimed in claim 2 , wherein each pipe comprises a boss with widened circular cross-section and wherein each hole made in said inner collar has a diameter corresponding to that of said boss, said hole accommodating said boss.
5. The compressor as claimed in claim 4 , wherein a channel is made between the edge of said inner collar and each hole, and wherein this channel has a width sufficient to fit said pipe into said hole.
6. The compressor as claimed in claim 2 , wherein an outer end of said pipe is fitted by sliding into the hole in said outer collar.
7. The compressor as claimed in claim 6 , wherein the outer end of each pipe, fitted in each respective hole of said outer collar, comprises a shoulder resting against the internal face of this outer collar.
8. The compressor as claimed in claim 1 , wherein said annular slot with lateral opening is defined in an annular rib projecting from the internal face of said inner collar.
9. The compressor as claimed in claim 8 , wherein each pipe comprises a boss with widened circular cross-section and wherein each hole made in said inner collar has a diameter corresponding to that of said boss, said hole accommodating said boss.
10. The compressor as claimed in claim 9 , wherein a channel is made between the edge of said inner collar and each hole, and wherein this channel has a width sufficient to fit said pipe into said hole.
11. The compressor as claimed in claim 8 , wherein an outer end of said pipe is fitted by sliding into the hole in said outer collar.
12. The compressor as claimed in claim 11 , wherein the outer end of each pipe, fitted in each respective hole of said outer collar, comprises a shoulder resting against the internal face of this outer collar.
13. The compressor as claimed in claim 8 , wherein said outer collar forms part of a wall delimiting the air stream.
14. An aircraft turbojet engine, said engine comprising a compressor as claimed in claim 8 .
15. The compressor as claimed in claim 1 , wherein each pipe comprises a boss with widened circular cross-section and wherein each hole made in said inner collar has a diameter corresponding to that of said boss, said hole accommodating said boss.
16. The compressor as claimed in claim 15 , wherein a channel is made between the edge of said inner collar and each hole, and wherein this channel has a width sufficient to fit said pipe into said hole.
17. The compressor as claimed in claim 1 , wherein an outer end of said pipe is fitted by sliding into the hole in said outer collar.
18. The compressor as claimed in claim 17 , wherein the outer end of each pipe, fitted in each respective hole of said outer collar, comprises a shoulder resting against the internal face of this outer collar.
19. The compressor as claimed in claim 1 , wherein said outer collar forms part of a wall delimiting the air stream.
20. An aircraft turbojet engine, said engine comprising a compressor as claimed in claim 1 .