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.
대표청구항▼
The invention claimed is: 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
The invention claimed is: 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.
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이 특허에 인용된 특허 (7)
Weiner Harvey I. (South Windsor CT) Allard Kenneth L. (Wilbraham MA), Active clearance control.
Quinones Armando J. (Cincinnati OH) Rieck ; Jr. Harold P. (West Chester OH) Albrecht Richard W. (Fairfield OH) Sullivan Michael A. (Ballston Spa NY) Weisgerber Robert H. (Loveland OH) Plemmons Larry , Turbine disk cooling system.
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