US 11,891,947 B2
Aircraft engine, gas turbine intake therefore, and method of guiding exhaust gasses
Guy Lefebvre, St-Bruno-de-Montarville (CA); Christopher Gover, Longueuil (CA); and Remy Synnott, Varennes (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jun. 23, 2022, as Appl. No. 17/808,385.
Prior Publication US 2023/0417174 A1, Dec. 28, 2023
Int. Cl. F02B 37/02 (2006.01); F01D 9/02 (2006.01); F04D 29/42 (2006.01); F04D 29/38 (2006.01)
CPC F02B 37/02 (2013.01) [F01D 9/026 (2013.01); F04D 29/386 (2013.01); F04D 29/42 (2013.01); F05D 2220/323 (2013.01)] 15 Claims
OG exemplary drawing
 
1. An aircraft engine comprising :
an exhaust conduit;
at least one combustion engine having an exhaust gas outlet fluidly connected to the exhaust conduit;
at least one gas turbine having a casing defining a radially outer limit of an annular gas path extending along and around a central axis, and at least one rotor having a shaft concentric to the central axis, a plurality of blades circumferentially interspaced from one another around the central axis and protruding radially from the shaft across the annular gas path; and
a gas turbine intake having a swirl housing having a tangential inlet fluidly connecting the exhaust conduit, an annular outlet fluidly connecting the annular gas path, a swirl path extending circumferentially around the central axis from the tangential inlet, and a plurality of vanes located in the swirl housing, the vanes circumferentially interspaced from one another relative the central axis, each vane having a twisted and flat body having a length extending from a leading end to a trailing end, the leading end being oriented mainly circumferentially and axially at the swirl path, the trailing end being oriented mainly axially and radially at the annular outlet, the twisted and flat body twisting between the leading end and the trailing end around the central axis and around a radial axis perpendicular to the central axis.