Turbine blade double tip flag cooling system

Patent metadata

Field	Value
Publication number	US-12467368-B1
Application number	US-202519011873-A
Country	US
Kind code	B1
Filing date	Jan 7, 2025
Priority date	Jan 7, 2025
Publication date	Nov 11, 2025
Grant date	Nov 11, 2025

Abstract

Systems provide enhanced cooling of tip regions of turbine blades. A cooling system includes a turbine blade with a root, a base, a tip, a leading edge, a trailing edge, an outer structure that includes a pressure side wall, a suction side wall and a tip cap at its tip. A core in the blade defines a leading channel that ejects cooling air through the leading edge. A primary tip flag channel ejects cooling air through the tip and the trailing edge. A secondary tip flag channel ejects cooling air through the trailing edge. The primary tip flag channel and the secondary tip flag channel promote cooling of the tip due to the locations in the tip area and their delivery of low temperature and high pressure cooling air thereto.

First claim

What is claimed is:

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.

2 . The cooling system of claim 1 , wherein the primary tip flag channel includes a throttle in the tip segment adjacent the trailing edge, wherein the throttle tapers the tip segment down and then flares larger to a slot exit at the trailing edge, and wherein the throttle is configured to increase internal pressure for cooling flow at the tip through tip cap film cooling holes and tip pressure side edge film cooling holes.

3 . The cooling system of claim 1 , wherein a tip edge is defined at a juncture between the tip cap and the pressure side wall, wherein a plurality of tip pressure side edge film cooling holes extend through the tip edge and into the primary tip flag channel, wherein the tip pressure side edge film cooling holes are supplied with cooling air solely by the primary tip flag channel.

4 . The cooling system of claim 3 , wherein a second tip edge is defined at a suction side of the tip cap, the second tip edge having an aerodynamically contoured radius.

5 . The cooling system of claim 1 , wherein pressure side film cooling holes are defined through the pressure side wall and into the primary tip flag channel and/or the secondary tip flag channel.

6 . The cooling system of claim 1 , comprising a showerhead defining a jet cavity and located between the leading cavity and the leading edge, the leading cavity ejecting the first part of the cooling air through the jet cavity, wherein the primary tip flag channel is not connected with the leading cavity so that the primary tip flag channel does not deliver any part of the cooling air through the leading edge which is supplied solely by the leading cavity.

7 . The cooling system of claim 1 , wherein the primary tip flag channel is defined, in entirety, by the first radial segment, the no more than one bend in the primary tip flag channel, and the tip segment, so that the second part of the cooling air passes from the base to the trailing edge through the first radial segment, the no more than one bend in the primary tip flag channel, and the tip segment, to provide a direct feed of the second part of the cooling air to the trailing edge with no more than a single turn, wherein the secondary tip flag channel is defined, in entirety, by the second radial segment, the no more than one bend in the secondary tip flag channel, and the sub-tip segment, so that the third part of the cooling air passes from the base to the trailing edge through the first radial segment, the no more than one bend in the secondary tip flag channel, and the sub-tip segment to provide a direct feed of the second part of the cooling air to the trailing edge with no more than a single turn.

8 . The cooling system of claim 1 , wherein the primary tip flag channel and the secondary tip flag channel are configured, through the first radial segment and the tip segment, and the second radial segment and the sub-tip segment, to deliver focused cooling to the tip and high-span trailing edge of the blade.

9 . The cooling system of claim 1 , wherein the number of conduits include a fourth conduit defining a trailing channel that includes a third radial segment extending from the base to a radially inner side of the secondary tip flag channel, wherein a pin bank cavity is defined between the third radial segment and the trailing edge, wherein the leading channel, the primary tip flag channel, the secondary tip flag channel and the trailing channel are all fluidly separate from one another and are independently tunable for flow without influencing each other.

10 . The cooling system of claim 1 , wherein the number of conduits include a fourth conduit defining a trailing channel that includes a third radial segment extending from the base to a radially inner side of the secondary tip flag channel, wherein a pin bank cavity is defined between the third radial segment and the trailing edge, wherein a number of crossover holes are distributed spanwise along the trailing channel and connect the trailing channel to the pin bank cavity, wherein the trailing channel is configured to eject a fourth part of the cooling air through the pin bank cavity and the trailing edge, wherein the fourth part of the cooing air is isolated from the second part of the cooling air in the primary tip flag channel and from the third part of the cooling air in the secondary tip flag channel.

11 . A cooling system for a turbine, the cooling system comprising:
at least one blade in the turbine that extends 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

Assignees

• Honeywell Int Inc

Inventors

• Kamrath Benjamin
• Crites Daniel
• Riahi Ardeshir
• Sperling Spencer
• Morris Mark

Classifications

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title