US 12,467,368 B1
Turbine blade double tip flag cooling system
Benjamin Kamrath, Mesa, AZ (US); Daniel Crites, Phoenix, AZ (US); Ardeshir Riahi, Phoenix, AZ (US); Spencer Sperling, Phoenix, AZ (US); and Mark Morris, Phoenix, AZ (US)
Assigned to HONEYWELL INTERNATIONAL INC., Charlotte, NC (US)
Filed by HONEYWELL INTERNATIONAL INC., Charlotte, NC (US)
Filed on Jan. 7, 2025, as Appl. No. 19/011,873.
Int. Cl. F01D 5/20 (2006.01); F01D 5/14 (2006.01); F01D 5/18 (2006.01)
CPC F01D 5/20 (2013.01) [F01D 5/141 (2013.01); F01D 5/18 (2013.01); F05D 2260/221 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A cooling system for a turbine, the cooling system comprising:
at least one blade extending from a root, the blade defined in a first direction between a base proximate the root and a tip distant the root, and the blade defined in a second direction from a leading edge to a trailing edge, wherein the blade has an outer structure that includes a pressure side wall and a suction side wall joining together at the leading edge and the trailing edge, and the blade including a tip cap at the tip and joining with the pressure side wall and the suction side wall;
a core in the blade within the pressure side wall, suction side wall and the tip cap, the core defining a number of conduits extending through the blade from the base to the trailing edge, the number of conduits channeling cooling air, and the number of conduits including:
a first conduit defining a leading channel that is substantially straight and that extends in a radial direction from the base to an end at the tip, wherein the leading channel is configured to eject a first part of the cooling air from the blade through the leading edge;
a second conduit defining a primary tip flag channel that is fluidly separated from the leading channel by a first common wall and that includes a first radial segment extending in a radial direction from the base to the tip and includes a tip section that extends from the first radial segment and runs along the tip to the trailing edge, the primary tip flag channel providing a direct route to the tip through the first radial segment and including no more than one bend in the primary tip flag channel between the base and the trailing edge, the primary tip flag channel spaced from the leading edge by the leading channel wherein the primary tip flag channel is configured to eject a second part of the cooling air from the blade through the trailing edge; and
a third conduit defining a secondary tip flag channel that is fluidly separated from the primary tip flag channel by a second common wall and that includes a second radial segment extending in the radial direction from the base to a radially inner side of the primary tip flag channel and includes a sub-tip segment extending from the second radial segment to the trailing edge, the secondary tip flag channel providing a direct route to a sub-tip area located radially inside the tip section through the second radial segment, and includes no more than one bend in the secondary tip flag channel between the base and the trailing edge, the sub-tip segment spaced away from the tip by the tip segment of the primary tip flag channel wherein the secondary tip flag channel is configured to eject a third part of the cooling air from the blade through the trailing edge;
wherein film cooling holes are defined through the tip cap and into the primary tip flag channel,
wherein the primary tip flag channel and the secondary tip flag channel are configured to promote cooling of the tip through locations of the tip segment and of the sub-tip segment.