US 11,852,034 B2
Tandem rotor blades
Matthew P. Forcier, South Windsor, CT (US); and Brian J. Schuler, West Hartford, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Mar. 23, 2020, as Appl. No. 16/827,135.
Application 16/827,135 is a continuation of application No. 14/882,722, filed on Oct. 14, 2015, granted, now 10,598,024.
Claims priority of provisional application 62/064,536, filed on Oct. 16, 2014.
Prior Publication US 2020/0217205 A1, Jul. 9, 2020
Int. Cl. F01D 5/14 (2006.01); F04D 29/32 (2006.01); F01D 9/04 (2006.01); F01D 11/00 (2006.01); F04D 29/54 (2006.01); F04D 19/02 (2006.01)
CPC F01D 5/146 (2013.01) [F01D 9/041 (2013.01); F01D 11/001 (2013.01); F04D 29/324 (2013.01); F04D 19/02 (2013.01); F04D 29/542 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2240/30 (2013.01); F05D 2240/55 (2013.01); F05D 2240/80 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A turbomachine comprising:
a stator vane stage;
a tandem blade stage aft of the stator vane stage, wherein the tandem blade stage includes:
a plurality of blade pairs, each blade pair of the plurality of blade pairs being circumferentially spaced apart from other blade pairs of the plurality of blade pairs, each blade pair of the plurality of blade pairs being operatively connected to a rotor disk disposed radially inward from the plurality of blade pairs, wherein each blade pair of the plurality of blade pairs includes a forward blade and an aft blade, wherein the aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween; and
a tandem stator vane stage aft of the tandem blade stage, the tandem stator vane stage including:
a vane platform secured to a portion of the turbomachine radially inward from the vane platform; and
at least one stator vane pair extending radially outward from the vane platform, the at least one stator vane pair includes a forward stator vane and an aft stator vane, wherein the vane platform of the tandem stator vane stage includes a forward portion that extends radially inward and towards the tandem blade stage aft of the stator vane stage; and
a plurality of circumferentially disposed blade platforms defined radially between the rotor disk and the plurality of blade pairs, wherein each blade pair of the plurality of blade pairs is integrally formed with a respective one of the blade platforms and wherein a forward portion of each of the plurality of circumferentially disposed blade platforms includes a forward platform extension that extends towards the stator vane stage and an aft portion of each of the plurality of circumferentially disposed blade platforms includes a first aft platform extension that extends directly from one of the aft blades of the plurality of blade pairs toward the tandem stator vane stage, a second aft platform extension that is disposed transverse to the first aft platform extension and is spaced apart from the rotor disk in a downstream direction and extends directly from the first aft platform extension toward the rotor disk, and an arcuate surface extending between the first aft platform extension and the second aft platform extension.