US 12,140,048 B1
Integrated centrifugal compressor diffuser and high pressure turbine vane assembly
Dave Menheere, Norval (CA); and Eduardo Hawie, Woodbridge (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Québec (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Dec. 15, 2023, as Appl. No. 18/541,606.
Int. Cl. F01D 9/04 (2006.01); B64D 33/02 (2006.01); F04D 29/28 (2006.01); F04D 29/44 (2006.01); F04D 29/54 (2006.01)
CPC F01D 9/04 (2013.01) [F04D 29/288 (2013.01); F04D 29/44 (2013.01); F04D 29/54 (2013.01); B64D 2033/0293 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a compressor section comprising an impeller configured to compress a core flow;
a combustor section comprising a combustor, wherein the combustor is arranged downstream from the compressor section along a path of the core flow; and
a turbine section arranged downstream from the combustor section along the path of the core flow, wherein the turbine section comprises a plurality of first vanes arranged at an outlet of the combustor, wherein at least one first vane of the plurality of first vanes comprises an internal vane path;
wherein the path of the core flow, in a flow direction, passes through the impeller of the compressor section, the internal vane path internal to the first vane, the combustor, and then between external surfaces of the plurality of first vanes to enter the turbine section.