US 9,810,074 B2
Segmented turbine blade squealer tip and cooling method
Ching-Pang Lee, Cincinnati, OH (US); Kok-Mun Tham, Oviedo, FL (US); and Gm Salam Azad, Oviedo, FL (US)
Appl. No. 15/318,001
Filed by Siemens Aktiengesellschaft, München (DE)
PCT Filed Jul. 7, 2014, PCT No. PCT/US2014/045512
§ 371(c)(1), (2) Date Dec. 12, 2016,
PCT Pub. No. WO2016/007116, PCT Pub. Date Jan. 14, 2016.
Prior Publication US 2017/0122110 A1, May 4, 2017
Int. Cl. F01D 5/18 (2006.01); F01D 5/14 (2006.01)
CPC F01D 5/187 (2013.01) [F01D 5/147 (2013.01); F05D 2220/32 (2013.01); F05D 2230/53 (2013.01); F05D 2240/307 (2013.01); F05D 2260/22141 (2013.01)] 17 Claims
OG exemplary drawing
1. A gas turbine engine blade squealer tip, comprising:
an airfoil planform tip plate having along its outer periphery downstream from its leading edge and upstream from its trailing edge opposed and laterally separated projecting concave pressure and convex suction rails respectively having inner and outer faces;
an enclosed tip cavity defined between the tip plate and respective inner faces of the pressure and suction rails from the leading to trailing edges;
at least one slot formed through respective inner and outer faces of the suction rail downstream of the leading edge, the slot in communication with the tip cavity and oriented for directing cooling air flow there through and downstream along the pressure rail inner face; and
a first tip fin projecting from the tip plate, having an upstream portion proximal the suction rail, a downstream portion oriented in the tip cavity and an outer face defining an upstream side of a first slot formed in the suction rail, the first tip fin oriented for directing cooling air flow through the first slot and downstream along the pressure rail inner face.