TURBOMACHINE, SUCH AS AVIATION TURBOJET ENGINE OR TURBOPROP ENGINE Russian patent published in 2017 - IPC F01D9/02 F01D11/00 F23R3/60 

FIELD: engine devices and pumps.

SUBSTANCE: subject of invention is a turbomachine such as an aircraft turbojet engine or a turboprop engine comprising an annular combustion chamber (1) defined by an inner shell (3) and an outer shell (4), a turbine directing apparatus (2) located downstream of annular combustion chamber (1), wherein the outlet end of the outer shell (4) and/or the inner shell (3) of the combustion chamber comprises the first radial flange (7) opposite the second radial flange (14) of directing apparatus inlet end (2), sealing means (16) comprising at least one sealing plate (17) between said flanges (7, 14) to provide sealing between the combustion chamber (1), and directing apparatus (2). The sealing plate (17) extends axially and circumferentially between said flanges (7, 14) and abuts radially into the free ends of said flanges (7, 14).

EFFECT: radial size of the combustion chamber flange can be reduced, which makes it possible to reduce the overall mass of the assembly and reduce the heat exchange surfaces with ambient air, the temperature of the outlet end of corresponding shell of the combustion chamber increases, thereby the temperature differences within this shell and the associated bending stresses reduce significantly.

11 cl, 9 dwg