Airfoils with lobed cooling cavities

Patent metadata

Field	Value
Publication number	US-12173618-B2
Application number	US-202318372955-A
Country	US
Kind code	B2
Filing date	Sep 26, 2023
Priority date	Sep 26, 2022
Publication date	Dec 24, 2024
Grant date	Dec 24, 2024

Abstract

A turbine engine airfoil element has a plurality of main body passageways along a camber line and having two or more chordwise distributed protuberant portions with necks between the protuberant portions. A plurality of skin passageways include: at least one first skin passageway each nested between a first of the pressure side and the suction side and two adjacent main body passageways; and a plurality of second skin passageways each nested between first of the pressure side and the suction side and two said protuberant portions of a corresponding main body passageway.

First claim

What is claimed is:

1. A turbine engine airfoil element comprising:
an airfoil having:
a pressure side and a suction side; and
a plurality of spanwise passageways including:
a plurality of main body passageways along a camber line and having two or more chordwise distributed protuberant portions and necks between the two or more chordwise distributed protuberant portions; and
a plurality of skin passageways including:
at least one first skin passageway each nested between a first of the pressure side and the suction side and two adjacent main body passageways; and
a plurality of second skin passageways each nested between said first of the pressure side and the suction side and two said protuberant portions of a corresponding main body passageway,

wherein:
the necks extend over at least 50% of a span of the airfoil;
the necks have a section within 10° of parallel to the adjacent first of the pressure side and the suction side and having an axial length L N between the airfoil leading edge and trailing edge of at least 0.030 inch (0.76 mm); and
the second skin passageways have a pair of side surfaces forming respective walls with adjacent surfaces of the associated protuberant portions, said walls having a central section diverging in thickness toward the camber line of the airfoil by an angle θ 4 of 3.0° to 10.0°.

2. The turbine engine airfoil element of claim 1 wherein:
viewed normal to the first of the pressure side and the suction side, each skin passageway overlaps its adjacent main body passageway depthwise.

3. The turbine engine airfoil element of claim 1 wherein:
the first of the pressure side and the suction side is the suction side so that the plurality of skin passageways are suction side passageways; and
the plurality of spanwise passageways further include:
a plurality of pressure side passageways including:
at least one first pressure side passageway each nested between the pressure side and two adjacent main body passageways; and
a plurality of second pressure side passageways each nested between the pressure side and two said protuberant portions of a corresponding main body passageway.

4. The turbine engine airfoil element of claim 3 wherein:
the pressure side passageways and the suction side passageways have rounded-corner triangular cross-section.

5. The turbine engine airfoil element of claim 3 wherein:
each of the protuberant portions has a rounded-corner quadrilateral planform.

6. The turbine engine airfoil element of claim 3 wherein:
adjacent pressure side passageways connect to each other via a plurality of linking passageways;
adjacent suction side passageways connect to each other via a plurality of linking passageways; and
the linking passageways extend less deeply into the airfoil cross-section than do the adjacent pressure or suction side passageways.

7. The turbine engine airfoil element of claim 3 wherein:
multiple of the second pressure side passageways and multiple of the second suction side passageways have:
one or more outboard projections into the respective pressure side wall or suction side wall; and
one or more inboard projections into a wall shared with the associated neck.

8. The turbine engine airfoil element of claim 3 being a blade having an attachment root:
the main body passageways extend from respective inlets at an inner diameter (ID) end of the attachment root; and
the first and second pressure side passageways and first and second suction side passageways extend from respective inlets at the inner diameter (ID) end of the attachment root.

9. A turbine engine including the turbine engine airfoil element of claim 3 .

10. A method for manufacturing the turbine engine airfoil element of claim 3 , the method comprising:
forming an assembly by assembling to each other:
a ceramic feedcore having sections for forming the plurality of main body passageways;
a ceramic pressure side skin core having sections for forming the plurality of pressure side passageways; and
a ceramic suction side skin core having sections for forming the plurality of suction side passageways;

overmolding the assembly with a fugitive;
shelling the fugitive to form a shell;
casting alloy in the shell; and
deshelling and decoring the cast alloy.

11. The turbine engine airfoil element of claim 1 wherein:
the turbine engine airfoil element is a blade having an attachment root.

12. The turbine engine airfoil element of claim 7 wherein:
the main body passageways extend from respective inlets at an inner diameter (ID) end of the attachment root; and
the first and second skin passageways extend from respective inlets at the inner diameter (ID) end of the attachment root.

13. A turbine engine airfoil element comprising:
an airfoil having:
a pressure side and a suction side; and
a plurality of spanwise passageways including:
a plurality of main body passageways along a camber line and having two or more chordwise distributed protuberant portions and necks between the two or more chordwise distributed protuberant portions; and
a plurality of skin passageways including:
at least one first skin passageway each nested between a first of the pressure side and the suction side and two adjacent main body passageways; and
a plurality of second skin passageways each nested between said first of the pressure side and the suction side and two said protuberant portions of a corresponding main body passageway,

wherein:
multiple of the second skin passageways have:
one or more outboard projections into the first of the pressure side wall and the suction side wall; and
one or more inboard projections into a wall shared with the associated neck.

14. The turbine engine airfoil element of claim 13 wherein:
the first of the pressure side and the suction side is the suction side so that the plurality of skin passageways are suction side passageways; and
the plurality of spanwise passageways further include:
a plurality of pressure side passageways including:
at least one first pressure side passageway each nested between the pressure side and two adjacent main body passageways; and
a plurality of second pressure side passageways each nested between the pressure side and two said protuberant portions of a corresponding main body passageway.

15. The turbine engine airfoil element of claim 14 wherein:
multiple of the second skin passageways have:
one or more outboard projections into the pressure side wall; and
one or more inboard projections into a wall shared with the associated neck.

16. The turbine engine airfoil element of claim 14 wherein:
viewed normal to the first of the pressure side and the suction side, each skin passageway overlaps its adjacent main body passageway depthwise.

17. The turbine engine airfoil element of claim 14 wherein:
the pressure side passageways and the suction side passageways have rounded-corner triangular cross-section.

18. The turbine engine airfoil element of claim 14 wherein:
each of the protuberant portions has a rounded-corner quadrilateral planform.

19. A turbine engine including the turbine engine airfoil element of claim 13 as a blade having an attachment root.

20. The turbine engine including the turbine engine airfoil element of claim 19 wherein:
the main body passageways extend from respective inlets at an inner diameter (ID) end of the attachment root; and
the first and second skin passageways extend from respective inlets at the inner

Assignees

• Rtx Corp

Inventors

• Spangler Brandon W
• Pack David R

Classifications

• F05D2260/202

  by film cooling · CPC title

• F05D2250/11

  triangular · CPC title

• F05D2240/301

  Cross-sectional characteristics · CPC title

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title