Manifold for turbine blade of gas turbine engine

Patent metadata

Field	Value
Publication number	US-12398644-B2
Application number	US-202318335206-A
Country	US
Kind code	B2
Filing date	Jun 15, 2023
Priority date	Jul 8, 2022
Publication date	Aug 26, 2025
Grant date	Aug 26, 2025

Abstract

A turbine blade includes a platform, a blade airfoil attached to one side of the platform, a blade root attached to the other side of the platform, a manifold attached to the blade root. The blade root defines a first cooling passage and a second cooling passage. The manifold includes an outer wall, a first compartment having a first flow area defined by a first aperture formed at the outer wall, and a second compartment having a second flow area defined by a second aperture formed at the outer wall. The first compartment meters a non-zero first flow of cooling air to the first cooling passage through the first flow area. The second compartment meters a non-zero second flow of cooling air to the second cooling passage through the second flow area that is different than the first flow area.

First claim

What is claimed is:

1. A turbine blade comprising:
a platform defining a first side and a second side;
a blade airfoil attached to the first side of the platform, the blade airfoil comprising a pressure side wall and a suction side wall defining a blade airfoil interior;
a blade root attached to the second side of the platform, the blade root including a blade root leading edge and a blade root trailing edge with respect to a flow direction of a working flow, the blade root defining a first cooling passage and a second cooling passage that are in flow communication with the blade airfoil interior; and
a manifold attached to the blade root, the manifold being non-planar, the manifold comprising:
an outer wall;
a first compartment having a first flow area defined by a first aperture, the first aperture being formed at the outer wall and open to the first compartment, the first compartment metering a non-zero first flow of cooling air to the first cooling passage through the first flow area; and
a second compartment having a second flow area defined by a second aperture, the second aperture being formed at the outer wall and open to the second compartment, the second compartment metering a non-zero second flow of cooling air to the second cooling passage through the second flow area that is different than the first flow area,
wherein the outer wall further comprises:
a first side plate that extends between the blade root leading edge and the blade root trailing edge;
a second side plate that extends between the blade root leading edge and the blade root trailing edge;
an outer plate that extends between the first side plate and the second side plate;
a forward plate attached to the first side plate, the second side plate, and the outer plate at one end; and
an aft plate attached to the first side plate, the second side plate, and the outer plate at the other end that is opposite to the one end,
wherein the outer plate is solid and spaced a non-zero distance away from a blade root end surface.

2. The turbine blade of claim 1 , wherein the manifold comprises a divider plate that is disposed between the forward plate and the aft plate, and wherein the divider plate divides the manifold into the first compartment and the second compartment.

3. The turbine blade of claim 1 , wherein the first aperture is formed at the first side plate.

4. The turbine blade of claim 1 , wherein the first compartment comprises a plurality of first apertures that are formed at the outer wall, and wherein the plurality of first apertures define the first flow area.

5. The turbine blade of claim 1 , wherein the blade root defines a third cooling passage that is in flow communication with the blade airfoil interior, wherein the manifold comprises a third compartment, wherein a portion of the outer wall that defines the third compartment is solid, and wherein the third compartment blocks the cooling air from entering the third cooling passage.

6. The turbine blade of claim 1 , wherein a perimeter of the manifold defines a planar surface arranged to attach to the blade root.

Assignees

• Siemens Energy Global Gmbh & Co Kg

Inventors

• Shteyman Yevgeniy P
• Gravett Phillip W
• Williamson Stephen

Classifications

• F01D5/3007

  of axial insertion type · CPC title

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F01D5/087 Primary

  in the radial passages of the rotor disc · CPC title