US 12,404,777 B1
Turbine support case with axial spokes and retaining members
Guy Lefebvre, St-Bruno-de-Montarville (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Oct. 1, 2024, as Appl. No. 18/903,268.
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 25/16 (2006.01); F01D 9/02 (2006.01); F01D 25/24 (2006.01)
CPC F01D 9/026 (2013.01) [F01D 25/162 (2013.01); F01D 25/24 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft engine, comprising:
a turbine including a turbine rotor rotatable about a central axis;
a scroll case having an inlet fluidly connected to a source of combustion gases and an outlet fluidly connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet;
a bearing housing extending around the central axis, the bearing housing including a support flange;
an exhaust case disposed downstream of the turbine; and
a turbine support case secured to the bearing housing and to the exhaust case, the turbine support case having spokes distributed around the central axis and extending along a direction having an axial component relative to the central axis, each of the spokes extending through the scroll case and radially supported by the bearing housing, a spoke of the spokes having a distal end secured to the support flange via:
one or more fasteners, and
a retaining member at the distal end of the spoke, the retaining member defining an abutment face facing an axial direction relative to the central axis and circumferentially overlapping the support flange, a portion of the support flange located axially between the distal end of the spoke and the abutment face.