US 12,480,452 B2
Aircraft dual-flow turbine engine assembly, the assembly being equipped with incidence-controlled air discharge fins
Eva Julie Lebeault, Moissy-Cramayel (FR); and Philippe Gérard Chanez, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/251,290
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Nov. 2, 2021, PCT No. PCT/FR2021/051918
§ 371(c)(1), (2) Date May 1, 2023,
PCT Pub. No. WO2022/096815, PCT Pub. Date May 12, 2022.
Claims priority of application No. 2011267 (FR), filed on Nov. 3, 2020.
Prior Publication US 2023/0407797 A1, Dec. 21, 2023
Int. Cl. F02C 9/00 (2006.01); F01D 17/12 (2006.01); F02C 6/08 (2006.01); F02C 9/18 (2006.01); F02K 1/66 (2006.01); F02K 1/74 (2006.01)
CPC F02C 9/18 (2013.01) [F01D 17/12 (2013.01); F02C 6/08 (2013.01); F02K 1/66 (2013.01); F02K 1/74 (2013.01); F05D 2220/323 (2013.01); F05D 2240/128 (2013.01); F05D 2260/60 (2013.01); F05D 2270/051 (2013.01)] 9 Claims
OG exemplary drawing
 
1. An aircraft dual-flow turbine engine assembly, comprising:
an inner shell configured to externally define a primary flow path of primary flow of an aircraft dual-flow turbine engine;
an outer shell configured to internally define a secondary flow path of secondary flow of the aircraft dual-flow turbine engine;
an air discharge duct extending between the inner shell and the outer shell, the air discharge duct opening into the secondary flow path through an outlet orifice equipped with discharge fins, wherein the discharge fins are movably mounted so as to be able to be incidence-controlled between a propulsion position, and a thrust reversal position,
wherein pitch axes of the discharge fins are arranged on a straight line;
wherein the aircraft dual-flow turbine engine assembly is designed to move the discharge fins in the propulsion position, such that a first discharge air flow, from the primary flow, is introduced into the secondary flow path from the outlet orifice along a first introduction direction comprising a first axial component from upstream to downstream, axially co-current with the secondary flow flowing in the secondary flow path of the aircraft dual-flow turbine engine in a normal propulsion configuration,
wherein the aircraft dual-flow turbine engine assembly is also designed to move the discharge fins in the thrust reversal position, such that a second discharge air flow, from the primary flow, is introduced into the secondary flow path from the outlet orifice along a second introduction direction comprising a second axial component from downstream to upstream, axially co-current with a counter-thrust gas flow flowing in the secondary flow path of the aircraft dual-flow turbine engine in a thrust reversal configuration,
wherein in the propulsion position, the discharge fins have first acute pitch angles, oriented in a first direction with respect to a longitudinal axis of the aircraft dual-flow turbine engine, and wherein in the thrust reversal position, the discharge fins have second acute pitch angles, oriented in a second direction with respect to the longitudinal axis of the aircraft dual-flow turbine engine, the second direction being opposite to the first direction, and
wherein in the thrust reversal position, the discharge fins of the air discharge duct have the second acute pitch angles with at least two different values oriented in the second direction, two end fins located respectively closest to two opposite axial ends of the outlet orifice of the air discharge duct having the second acute pitch angles of values greater than that of at least one other discharge fin located axially between the two end fins.