Component with cooling passage for a turbine engine

Patent metadata

Field	Value
Publication number	US-12571317-B2
Application number	US-202418668840-A
Country	US
Kind code	B2
Filing date	May 20, 2024
Priority date	Oct 1, 2021
Publication date	Mar 10, 2026
Grant date	Mar 10, 2026

Abstract

An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.

First claim

What is claimed is:

1 . A blade for a turbine engine, the blade comprising:
an outer wall including an outer surface, the outer wall including an upstream edge, a downstream edge, a root and a tip, the outer surface including a first side and a second side, wherein the first side is separated from the second side at the upstream edge and the downstream edge; a tip wall defining an interior and a plenum at the tip; a tip rail defining the plenum; a cooling conduit; and multiple cooling passages fluidly coupling the cooling conduit to the outer surface, each of the multiple cooling passages comprising: a diffusion slot including: an intermediate outlet; a passage outlet in the outer surface, wherein the passage outlet is elongated; a rear, a front, wherein the passage outlet is at the front and the intermediate outlet is adjacent the rear; and an impingement surface opposite the intermediate outlet; and wherein each of the diffusion slots have a diffuser vector and wherein at least two adjacent diffuser vectors are different, the at least two adjacent diffuser vectors pointing increasingly toward the downstream edge, when moving from the upstream edge to the downstream edge.

2 . The blade of claim 1 , wherein the diffusion slot defines a slot centerline extending between an intermediate center of the intermediate outlet and an outlet center of the passage outlet.

3 . The blade of claim 2 , wherein the slot centerline forms a first angle of between +/−70°, inclusive of endpoints with a radial direction such that the diffusion slot points toward a leading edge or a trailing edge.

4 . The blade of claim 2 , wherein each cooling passage of the multiple cooling passages further comprises a metered passage including:
an inlet fluidly connected to the cooling conduit; and the respective intermediate outlet is fluidly coupled to a respective diffusion slot at a junction proximate a rear of the diffusion slot, and defining a first centerline, which forms an angle relative to the slot centerline.

5 . The blade of claim 4 , wherein the intermediate outlet is spaced from the rear to define a pocket.

6 . The blade of claim 1 , wherein the passage outlet is on a concave side of the blade.

7 . The blade of claim 1 wherein at least one of the multiple cooling passages fluidly couple the cooling conduit to an inner tip rail surface.

8 . The blade of claim 1 , wherein the passage outlet is on an outer tip rail surface.

9 . The blade of claim 1 , wherein respective diffusion slots of the multiple cooling passages are arranged in a fanning layout.

10 . The blade of claim 1 , wherein passage outlets of respective diffusion slots of the multiple cooling passages are spaced from one another.

11 . The blade of claim 1 , wherein passage outlets respective diffusion slots of the multiple cooling passages are combined in a trench.

12 . The blade of claim 1 , wherein the diffuser vector of each of the multiple cooling passages is varied.

13 . The blade of claim 1 , wherein the passage outlet is located at an outer tip rail surface.

14 . The blade of claim 1 , wherein at least some of the multiple cooling passages include corresponding diffuser vectors pointing increasingly toward the downstream edge as the multiple cooling passages are arranged from the upstream edge toward the downstream edge.

15 . The blade of claim 1 , wherein a length of a respective diffusion slot of at least two of the multiple cooling passages varies.

16 . The blade of claim 1 , further comprising a second set of cooling passages formed in the outer wall and fluidly coupling the cooling conduit to the outer surface, at least one of the cooling passages in the second set of cooling passages comprising a diffusion slot extending in a flow direction toward the tip and terminating in a passage outlet opening onto an upper tip rail surface.

17 . A blade for a turbine engine, the blade comprising:
an outer wall including an outer surface, the outer wall including an upstream edge, a downstream edge, a root, and a tip, the outer surface including a first side and a second side, wherein the first side is separated from the second side at the upstream edge and the downstream edge; a tip wall defining an interior and a plenum at the tip; a tip rail defining the plenum; a cooling conduit; and multiple cooling passages fluidly coupling the cooling conduit to the outer surface, each of the multiple cooling passages comprising: a diffusion slot including an intermediate outlet, a passage outlet in the outer surface, wherein the passage outlet is elongated, a rear, a front, wherein the passage outlet is at the front and the intermediate outlet is adjacent the rear, and an impingement surface opposite the intermediate outlet, and wherein at least some of the diffusion slots include corresponding diffuser vectors arranged in a fanning layout.

18 . The blade of claim 17 , wherein each diffusion slot includes corresponding diffuser vectors arranged in the fanning layout.

19 . The blade of claim 17 , wherein each diffusion slot has a corresponding diffuser vector pointing increasingly toward the downstream edge as the multiple cooling passages are arranged from the upstream edge toward the downstream edge.

Assignees

• Gen Electric

Inventors

• Webster Zachary Daniel
• Osgood Daniel Endecott
• Gallier Kirk Douglas

Classifications

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F01D5/087

  in the radial passages of the rotor disc · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2260/232

  characterized by the cooling medium · CPC title