Cooled single walled blisk for gas turbine engine

Patent metadata

Field	Value
Publication number	US-2018230833-A1
Application number	US-201715405508-A
Country	US
Kind code	A1
Filing date	Jan 13, 2017
Priority date	Jan 13, 2017
Publication date	Aug 16, 2018
Grant date	—

Abstract

A gas turbine engine and a blisk are disclosed, including methods of making the same. The blisk may include a disk, spars of airfoils, platforms, and shanks of the airfoils integrally formed as a unit. Such blisk features may be integrally formed by a casting process or additive manufacturing. The blisk includes cooled airfoils, such that the spar includes standoffs, and a cover panel is bonded to an outer surface of the standoffs to define passages between the cover panel and the spar. Cooling air is fed through an inlet port formed in a base standoff to the passages of the spar through a cooling feed channel defined in the disk or shank portion.

First claim

What is claimed is:

1 . A blisk for a gas turbine engine having a longitudinal axis, the blisk comprising a disk, a spar, a platform, and a shank portion integrally formed as a unit, the disk disposed about a longitudinal axis and having an upstream side and a downstream side, the spar extending radially outward from the platform relative to the longitudinal axis, the shank portion extending between the platform and the disk, wherein the spar includes a plurality of standoffs extending away from an outer surface of the spar, wherein the blisk further comprises a cover panel bonded to an outer surface of the standoffs, wherein the standoffs are spaced from one another such that a plurality of cooling flow passages are defined between the cover panel and the spar, the spar including a base standoff disposed along the platform, the base standoff comprising an inlet port defined in the base standoff in communication with the cooling flow passages, the cover panel having one or more discharge ports defined therein in communication with the cooling flow passages, wherein a cooling feed channel is defined in the disk or shank portion and in communication with the inlet port, wherein the cooling feed channel is configured to receive cooling air upstream of the disk for delivery to the cooling flow passages.

2 . The blisk of claim 1 , wherein the spar includes a suction side and a pressure side, wherein the base standoff is located along at least one of the pressure side and the suction side.

3 . The blisk of claim 2 , wherein the inlet port is a first inlet port associated with the pressure side, the spar comprising a second inlet port defined in a second base standoff located along the suction side.

4 . The blisk of claim 1 , wherein a downstream end of the cooling feed channel spans a width of the spar to communicate with the first and second inlet ports.

5 . The blisk of claim 1 , wherein the inlet port is a first inlet port, the spar including a second inlet port defined in the base standoff, wherein the second inlet port is disposed closer to a trailing edge of the spar than the first inlet port.

6 . The blisk of claim 5 , wherein the cooling feed channel includes a first branch in communication with the first inlet port and a second branch in communication with the second inlet port.

7 . The blisk of claim 6 , wherein the spar includes a radial separator wall to divide the spar between a body section and a trailing section, wherein the first inlet port is associated with the body section and the second inlet port is associated with the trailing section.

8 . The blisk of claim 1 further comprising an upstream rim, wherein the cooling feed channel extends through the upstream rim.

9 . The blisk of claim 1 , wherein the disk, the spar, the platform, and the shank portion are a casted unit.

10 . The blisk of claim 1 , wherein the spar, the platform, and the shank portion are a successively layered formed unit.

11 . The blisk of claim 1 , wherein the cooling feed channel includes an inlet formed in the upstream side of the disk or the shank portion.

12 . The blisk of claim 1 , wherein the cover panel comprises a single sheet.

13 . The blisk of claim 1 , wherein the cover panel comprises a suction side panel and a pressure side panel.

14 . A method of making a blisk for a gas turbine engine, the method comprising:
forming a disk, a spar, a platform, and a shank portion integrally as a unit, wherein the spar extends radially outward from the platform, the shank portion extends between the platform and the disk, wherein the spar includes a plurality of standoffs extending away from an outer surface of the spar, the standoffs spaced away from one another such that cooling passages are defined therebetween, and an inlet port defined in a base standoff in communication with the cooling passages, wherein a cooling feed channel is defined in the disk or shank portion and in communication with the cooling air passages; and coupling a cover panel to an outer surface of the standoffs.

15 . The method of claim 14 , wherein the unit formed is formed as a casted unit.

16 . The method of claim 14 , wherein the forming includes: forming the disk; providing a computer-readable three-dimensional model of the spar, the platform, and the shank portion, the three-dimensional model configured to be converted into a plurality of slices that each define a cross-sectional layer of at least one of the spar, the platform, and the shank portion; and successively forming each layer directly on the disk by additive manufacturing.

17 . The method of claim 14 , wherein the forming and the coupling include: forming the disk; providing a computer-readable three-dimensional model of the spar, the platform, the shank portion, and the cover panel, the three-dimensional model configured to be converted into a plurality of slices that each define a cross-sectional layer of at least one of the spar, the platform, the shank portion, and the cover panel; and successively forming each layer directly on the disk by additive manufacturing.

18 . A gas turbine engine having longitudinal axis, the gas turbine engine comprising a turbine section including a blisk, the blisk including a disk, a spar, a platform, and a shank portion integrally formed as a unit, the disk disposed about a longitudinal axis and having an upstream side and a downstream side, the spar extending radially outward from the platform relative to the longitudinal axis, the shank portion extending between the platform and the disk, wherein the spar includes a plurality of standoffs extending away from an outer surface of the spar, wherein the blisk further comprises a cover panel bonded to an outer surface of the standoffs, wherein the standoffs are spaced from one another such that a plurality of cooling flow passages are defined between the cover panel and the spar, the spar comprising an inlet port defined in a base standoff in communication with the cooling flow passages, the cover panel having one or more discharge ports defined therein in communication with the cooling flow passages, wherein a cooling feed channel is defined in the disk or shank portion and in communication with the inlet port, wherein the cooling feed channel is configured to receive cooling air upstream of the disk for delivery to the cooling flow passages.

19 . The gas turbine engine of claim 18 , wherein the disk, the spar, the platform, and the shank portion are a casted unit.

20 . The gas turbine engine of claim 18 , wherein the spar, the platform, and the shank portion are a successively layered formed unit.

Assignees

• Rolls Royce Corp

Inventors

• Kush Matthew T

Classifications

• F05D2230/31

  Layer deposition · CPC title

• F01D5/34 Primary

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title