Air intake circuit arrangement for high pressure compressor of a turbine engine
View Patent ↗In a compressor stage including a movable bladed wheel having movable blades and a fixed bladed wheel having fixed blades, an air tapping circuit arrangement includes a movable wheel manifold designed to collect an air flow aspirated from the movable blades and a fixed wheel manifold designed to collect an air flow aspirated from the fixed blades. The movable wheel manifold is placed on the periphery of the compressor stage facing the movable wheel and the fixed wheel manifold is superposed on the movable wheel manifold.
1. An air tapping circuit arrangement of a compressor stage of a turbojet, said compressor stage comprising a movable bladed wheel having movable blades and a fixed bladed wheel having fixed blades, said circuit arrangement comprising:
a movable wheel manifold designed to collect an air flow aspirated from the movable blades, said movable wheel manifold being in fluid communication with a first plurality of tapping orifices facing said movable bladed wheel and provided on an outer casing of said compressor stage; and
a fixed wheel manifold designed to collect an air flow aspirated from the fixed blades, said fixed wheel manifold being in fluid communication with a second plurality of tapping orifices facing said fixed bladed wheel and provided on said outer casing of said compressor stage; and
an adapter part including a first duct section extending in a substantially radial direction, a second duct section extending in a substantially transverse direction, a third duct section, and a substantially cylindrical body which extends about said first duct section, said first duct section being only in fluid communication with said movable wheel manifold, and said second and third duct sections being only in fluid communication with said fixed wheel manifold,
wherein said movable wheel manifold is placed on a periphery of said compressor stage facing said movable wheel and said fixed wheel manifold is superposed on said movable wheel manifold,
wherein a first end of said first duct section is connected to said movable wheel manifold and a second end of said first duct section is connected to a first conveyor pipe which conveys air tapped from said movable blades to other portions of said turbojet,
wherein said second duct section is divided into two halves which connect on either side of said body, a first end of each of said halves is connected to said body and a second end of each of said halves is connected to said fixed wheel manifold, and
wherein a first end of said third duct section is connected to said body so as to be in fluid communication with said second duct section and a second end of said third duct section is connected to a second conveyor pipe which conveys air tapped from said fixed blades to other portions of said turbojet.
2. The circuit arrangement as claimed in claim 1 , further comprising connecting tubes that each connect the periphery of the compressor stage facing the fixed wheel to the fixed wheel manifold.
3. The circuit arrangement as claimed in claim 2 , wherein said fixed wheel manifold comprises connecting orifices into which said connecting tubes are connected.
4. The circuit arrangement as claimed in claim 1 , wherein said first duct section traverses said second duct section.
5. The circuit arrangement as claimed in claim 1 , wherein said first duct section, second duct section and third duct section extend in directions that are perpendicular in pairs.
6. The circuit arrangement as claimed in claim 1 , wherein said adapter part further comprises connection means for connecting said adapter part to other elements of said circuit arrangement.
7. The circuit arrangement as claimed in claim 6 , wherein said connection means comprise a threading of the first end of the first duct section.
8. The circuit arrangement as claimed in claim 6 , wherein said connection means comprise a plate for fixing the second end of the first duct section.
9. The circuit arrangement as claimed in claim 6 , wherein said connection means comprise specific dimensions of the second end of each of said halves of the second duct section that allow a forced engagement of each of said second end of each of said halves in the fixed wheel manifold.
10. A compressor stage, which comprises an air tapping circuit arrangement as claimed in claim 1 .
11. A compressor, which comprises at least one air tapping circuit arrangement as claimed in claim 1 .
12. A turbojet, which comprises at least one air tapping circuit arrangement as claimed in claim 1 .
13. The circuit arrangement as claimed in claim 1 , wherein the third duct extends in a substantially axial direction.