Turbine blisk with airfoil and rim cooling

Patent metadata

Field	Value
Publication number	US-10718218-B2
Application number	US-201815911367-A
Country	US
Kind code	B2
Filing date	Mar 5, 2018
Priority date	Mar 5, 2018
Publication date	Jul 21, 2020
Grant date	Jul 21, 2020

Abstract

A blisk for a turbine engine is provided, the blisk includes a hub, a rim positioned radially outward from the hub, and a blade. The rim an outer surface facing radially outward from the hub and an inner surface. The blade is integral to the rim and includes a leading end, a trailing end, an interior surface, and a radially inward end. A cooling passage extends from an inlet in the inner surface of the rim, from the inlet through a channel enclosed within the rim and extending along the outer surface of the rim, and from the channel through an opening at the trailing end of the blade into a chamber defined by the interior surface of the blade.

First claim

What is claimed is:

1. A blisk for use in a turbine section of a gas turbine engine, the blisk comprising:
a hub;
a rim positioned radially outward from the hub, wherein the rim comprises a first leading end, a first trailing end, an outer surface facing radially outward from the hub, and an inner surface; and
a blade integral to the rim, the blade comprising a second leading end, a second trailing end, an interior surface defining a chamber within the blade, and a radially inward end, wherein a cooling passage extends from an inlet defined in the inner surface of the rim proximate the first leading end, from the inlet through a channel enclosed within the rim and extending along the outer surface of the rim from proximate the first leading end to proximate the first trailing end where an opening is proximate the first trailing end of the rim and the second trailing end of the blade, the cooling passage extending between the channel and the chamber through the opening, and wherein the channel is separated from the chamber except at the opening.

2. The blisk of claim 1 , further comprising a plurality of blades comprising the blade, and a plurality of channels comprising the channel, wherein each blade of the plurality of blades is spaced apart from each other on the outer surface of the rim, and wherein each channel of the plurality of channels extends along a portion of the outer surface of the rim which is arranged between a pair of the plurality of blades.

3. The blisk of claim 1 , wherein the channel comprises a first channel further extending along a portion of the outer surface of the rim which is proximate to a pressure side of the blade, the blisk further comprising a second channel extending along a portion of the outer surface of the rim which is proximate to a suction side of the blade.

4. The blisk of claim 3 , wherein the blade comprises a first blade, the suction side comprising a first suction side, the portion of the outer surface of the rim comprising a first portion of a first outer surface of a first rim, the cooling passage comprising a first cooling passage, and wherein the first channel is adjacent to a third channel extending along a second portion of a second outer surface of a second rim of a second blade proximate to a second suction side of the second blade.

5. The blisk of claim 1 , wherein the blisk is a unitary body formed from a single casting.

6. The blisk of claim 5 , wherein the blisk comprises a nickel-based superalloy.

7. A turbine section for use in a gas turbine engine, comprising:
a blisk comprising a hub and a rim positioned radially outward from the hub, wherein the rim comprises a first end, a second end, an outer surface extending from the first end to the second end, and an inner surface, and a blade integral to the rim, the blade comprising a leading end proximate to the first end of the rim, a trailing end proximate to the second end of the rim, an interior surface defining a chamber, a radially inward end, and a radially outward surface opposed to the radially inward end;
wherein a cooling passage extends from an inlet defined by the inner surface at the first end of the rim to a channel enclosed in the rim, the channel extending from the first end to the second end where an opening into the chamber of the blade is proximate to the trailing end of the blade, wherein the channel is separated from the chamber except at the opening, and wherein the cooling passage further extends from the chamber through an outlet in the radially outward surface at the leading end of the blade;
a cooling source configured to supply fluid to the inlet of the cooling passage; and
a vent configured to receive fluid from the outlet of the cooling passage.

8. The turbine section of claim 7 , wherein the chamber is configured to allow unobstructed flow of fluid from the trailing end to the leading end of the blade.

9. The turbine section of claim 8 , wherein the interior surface of the blade comprises a strut extending through the chamber from a pressure side of the blade to a suction side of the blade.

10. The turbine section of claim 8 , wherein the interior surface of the blade defines an opening at the leading end of the blade, wherein the opening is configured to allow fluid communication between the chamber and an exterior surface of the blade.

11. The turbine section of claim 7 , wherein the interior surface of the blade comprises a first wall extending radially outward from a radially inward end of the interior surface and a second wall extending radially inward from a radially outward end of the interior surface.

12. The turbine section of claim 11 , wherein the second wall is positioned closer to the outlet of the cooling passage than the first wall, such that fluid passing through the chamber must make three passes between the radially inward end and the radially outward end of the interior surface between the opening of the chamber and the outlet of the cooling passage.

13. A blisk for use in a turbine section of a gas turbine engine, the blisk comprising:
a hub;
a rim positioned radially outward from the hub, wherein the rim comprises a leading end, a trailing end, an outer surface facing radially outward from the hub, and an inner surface; and
a blade extending radially outward from the outer surface of the rim, the blade comprising an interior surface defining a chamber within the blade,
wherein a cooling passage extends from an inlet defined in the inner surface of the rim proximate the leading end, from the inlet through a channel enclosed within the rim and extending along the outer surface of the rim from proximate the leading end to proximate the trailing end where an opening into a chamber is located, wherein the channel is separated from the chamber except at the opening, wherein the hub, the rim, the blade, and the interior surface are a unitary body and formed from a single casting.

14. The blisk of claim 13 , wherein the interior surface of the blade comprises a strut extending through the chamber from a pressure side of the blade to a suction side of the blade.

15. The blisk of claim 14 , wherein the interior surface of the blade comprises a plurality of struts extending through the chamber, the plurality of struts arranged within the chamber to evenly distribute fluid passing through the chamber.

16. The blisk of claim 14 , wherein the strut is integrally formed to the interior surface of the blade.

17. The blisk of claim 13 , wherein the interior surface of the blade further comprises a bleed hole positioned on a leading edge of the blade and extending between the chamber and an outer surface of the blade.

18. The blisk of claim 13 , wherein the cooling passage is divided between a pressure side channel which extends along the outer surface of the rim on a pressure side of the blade and a suction side channel which extends along the outer surface of the rim on a suction side of the blade.

19. The blisk of claim 18 , wherein the pressure side channel and the suction side channel are both in fluid communication with the same inlet at a leading end of the blade.

20. The blisk of claim 18 , wherein the pressure side channel and the suction side channel are both in fluid communication with the same chamber at the trailing end of the blade.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Dierksmeier Douglas D

Classifications

• Y02T50/60

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

• F05D2220/32

  in gas turbines · CPC title

• F05D2230/10

  by removing material · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/24

  for turbines · CPC title