US 11,815,020 B2
Tangential on-board injector (TOBI) assembly
Gabriel Naccache, Longueuil (CA); Christopher Gover, Longueuil (CA); Alexander Smith, Montréal (CA); Alain Martel, St-Paul d'Abbotsford (CA); and Matthieu Boudreau, Montréal (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jul. 20, 2022, as Appl. No. 17/813,745.
Application 17/813,745 is a division of application No. 16/656,750, filed on Oct. 18, 2019, granted, now 11,421,597.
Prior Publication US 2022/0356842 A1, Nov. 10, 2022
Int. Cl. F01D 5/08 (2006.01); F02C 7/12 (2006.01); F02C 7/22 (2006.01)
CPC F02C 7/12 (2013.01) [F01D 5/081 (2013.01); F01D 5/082 (2013.01); F02C 7/22 (2013.01); F05D 2220/32 (2013.01); F05D 2240/35 (2013.01); F05D 2240/55 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A tangential on-board injector (TOBI) of a gas turbine engine, comprising:
a body defining an annular passageway configured to receive cooling air, the TOBI defining a plurality of discharge nozzles each having an outlet and defining an exit flow axis at the outlet;
a rotating component configured to be mounted for rotation relative to the body about an axis of rotation;
a seal extending between the body and the rotating component;
a plurality of vanes circumferentially distributed about the axis of rotation and located downstream of the plurality of discharge nozzles relative to a flow of the cooling air circulating toward the seal from the plurality of discharge nozzles and upstream of the seal, the plurality of vanes being radially offset from the plurality of discharge nozzles relative to the exit flow axis; and
flow passages defined between the plurality of vanes, a flow passage of the flow passages extending along a passage axis, the passage axis having a tangential component at an outlet of the flow passage that is less than a tangential component of the exit flow axis of each nozzle of the plurality of discharge nozzles.