US 12,352,205 B2
Turbojet with improved air extraction performance
Nicolas Claude Parmentier, Moissy-Cramayel (FR); and William Henri Joseph Riera, Moissy-Cramayel (FR)
Assigned to SAFRAN, Paris (FR)
Appl. No. 18/249,417
Filed by SAFRAN, Paris (FR)
PCT Filed Oct. 19, 2021, PCT No. PCT/FR2021/051812
§ 371(c)(1), (2) Date Apr. 18, 2023,
PCT Pub. No. WO2022/084614, PCT Pub. Date Apr. 28, 2022.
Claims priority of application No. 2010716 (FR), filed on Oct. 19, 2020.
Prior Publication US 2024/0110523 A1, Apr. 4, 2024
Int. Cl. F02C 6/08 (2006.01); F02C 9/18 (2006.01)
CPC F02C 6/08 (2013.01) [F02C 9/18 (2013.01)] 7 Claims
OG exemplary drawing
 
1. An aircraft turbojet comprising, in succession, from upstream to downstream in a circulation direction of a primary air stream:
a low-pressure casing, an intermediate casing and a high-pressure casing which are aligned entirely in a longitudinal direction, the low-pressure, intermediate and high-pressure casings jointly delimiting an internal annular passage for circulation of the primary air stream from upstream to downstream, the intermediate casing comprising a portion of said internal annular passage which is called a gooseneck portion, the intermediate casing comprising:
an air discharge system which is able to extract air from the primary air stream circulating in a first zone of the gooseneck portion and to discharge the air outside of the internal annular passage,
an air extraction system which is able to extract the air from the primary air stream circulating in a second zone of the gooseneck portion, the extracted air being intended for an aircraft air conditioning system, the second zone being located downstream of the first zone, and
in the gooseneck portion are a total number of arms which each extend radially and with a circumferential distribution in the gooseneck portion when viewed in a transverse plane relative to the longitudinal direction, the total number of arms is divided into at least one first set of the arms and at least one second set of the arms, each of the at least one second set of the arms is a different set from each of the at least one first set of the arms,
the air extraction system comprising the at least one first set of the arms, each arm of the at least one first set of the arms is configured to extract the air from the second zone by at least one slot in a leading edge of the arm and to route the extracted air, said at least one slot extending from a base of the arm in a radial extension direction over a distance which represents between 30% and 70% of a total radial extension of the arm,
wherein the air extraction system comprises at least one air manifold which is fluidly isolated from the air discharge system,
wherein each of said at least one air manifold is connected to a respective one of the at least one first set of the arms and is configured to collect the air extracted and routed by said respective one of the at least one first set of the arms,
wherein each of said at least one air manifold extends circumferentially over a respective angular sector less than 360° which corresponds to a respective first circumferential extent of the respective one of the at least one first set of the arms, and
wherein in the gooseneck portion, each arm of the at least one second set of the arms provides structural support and is located within a respective second circumferential extent adjacent to each first circumferential extent, and each arm of the at least one second set of the arms is not configured to extract the air from the second zone.