US 12,173,646 B2
Constant volume turbomachine combustion chamber
Didier René André Escure, Moissy-Cramayel (FR); and Nicolas Jérôme Jean Tantot, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/626,637
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jul. 8, 2020, PCT No. PCT/FR2020/051211
§ 371(c)(1), (2) Date Jan. 12, 2022,
PCT Pub. No. WO2021/009439, PCT Pub. Date Jan. 21, 2021.
Claims priority of application No. 1907970 (FR), filed on Jul. 15, 2019.
Prior Publication US 2022/0260012 A1, Aug. 18, 2022
Int. Cl. F02C 5/12 (2006.01); F23R 7/00 (2006.01)
CPC F02C 5/12 (2013.01) [F23R 7/00 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A combustion chamber of an aircraft turbomachine having a main axis and including:
a body of revolution coaxial with the main axis in which a plurality of combustion tubes are formed, said combustion tubes extending mainly in the direction of the main axis of the body and being distributed in a ring about said main axis,
a first perforated rotary disc which is mounted at a first axial end of the body and which is movable in rotation about the main axis to selectively open or close a first end of each of said combustion tubes, and
a second perforated rotary disc which is mounted at a second axial end of the body and which is movable in rotation about the main axis to selectively open or close a second end of each of said combustion tubes,
wherein the body includes a plurality of cooling segments which extend mainly in the direction of the main axis, which are distributed in a ring about said main axis and around the combustion tubes and are configured to cool a radially outer portion of the body, and
wherein each cooling segment is open at each axial end of the body and is passed through by a compressed air flow,
wherein each rotary disc is coaxial with the main axis, includes a series of lumens intended to face one end of each combustion tube and in a selective manner, and includes a series of orifices intended to face one end of each cooling segment in a selective manner,
wherein each rotary disc is configured to selectively open or close a corresponding end of the cooling segments when the orifices are facing an associated axial end of the cooling segments.