Geared gas turbine engine

Patent metadata

Field	Value
Publication number	US-10508550-B2
Application number	US-201715793454-A
Country	US
Kind code	B2
Filing date	Oct 25, 2017
Priority date	Oct 25, 2017
Publication date	Dec 17, 2019
Grant date	Dec 17, 2019

Abstract

An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.

First claim

What is claimed is:

1. An airfoil array comprising:
an endwall;
a first airfoil and a second airfoil each extending radially from the endwall and having a first side and an opposite second side extending along an axially chord between a leading edge and a trailing edge;
a first profiled region recessed into the endwall at an intersection with the first side of the first airfoil;
a second profiled region protruding from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil; and
a third profiled region recessed into the endwall along adjacent the leading edge of the second side of the second airfoil, wherein the third profiled region is at least partially axially aligned with the second profiled region.

2. The array of claim 1 , wherein the first profiled region extends approximately 100% of the axial chord.

3. The array of claim 2 , wherein the first profiled region extends approximately 30% of the pitch between the first airfoil and the second airfoil.

4. The array of claim 3 , wherein the first profiled region includes a lower most surface located in a forward 30% of the axial chord.

5. The array of claim 1 , wherein the third profiled region extends along approximately a forward 30% of the axial chord and extends along approximately 30% of the pitch between the first airfoil and the second airfoil.

6. The array of claim 1 , including a fourth profiled region protruding from the endwall along the second side of the second airfoil downstream from the third profiled region.

7. The array of claim 6 , including a fifth profiled region protruding from the endwall along the first side of the first airfoil upstream of the first profiled region.

8. The array of claim 7 , wherein the fourth profiled region extends along approximately an aft 50% axial chord and extends along approximately 50% of the pitch between the first airfoil and the second airfoil.

9. The array of claim 8 , wherein the fifth profiled region extends along approximately a forward 10% of the axial chord and extends along approximately 10% of the pitch between the first airfoil and the second airfoil.

10. The array of claim 1 , wherein the second profiled region extends along approximately a forward 30% of the axial chord and extends along approximately 30% of the pitch between the first airfoil and the second airfoil.

11. An airfoil array comprising:
an endwall;
a first airfoil and a second airfoil each extending radially from the endwall and having a first side and an opposite second side extending along an axially chord between a leading edge and a trailing edge;
a first profiled region recessed into the endwall along the first side of the first airfoil;
a second profiled region protruding from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil, wherein the second profiled region extends along approximately a forward 30% of the axial chord and extends along approximately 30% of the pitch between the first airfoil and the second airfoil; and
a third profiled region recessed into the endwall along adjacent the leading edge of the second side of the second airfoil, wherein the third profiled region is at least partially axially aligned with the second profiled region.

12. A gas turbine engine, comprising:
a compressor section; and
a turbine section located downstream of the compressor section, wherein at least one of the compressor section or the turbine section includes an array of airfoils including:
an endwall;
a first airfoil and a second airfoil each extending radially from the endwall and having a first side and an opposite second side extending along an axially chord between a leading edge and a trailing edge;
a first profiled region recessed into the endwall along the first side of the first airfoil;
a second profiled region protruding from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil; and
a third profiled region recessed into the endwall along adjacent the leading edge of the second side of the second airfoil, wherein the third profiled region is at least partially axially aligned with the second profiled region, wherein the third profiled region extends along approximately a forward 30% of the axial chord and extends along approximately 30% of the pitch between the first airfoil and the second airfoil.

13. The gas turbine engine of claim 12 , wherein the first profiled region extends approximately 100% of the axial chord.

14. The gas turbine engine of claim 13 , wherein the first profiled region extends approximately 30% of the pitch between the first airfoil and the second airfoil.

15. The gas turbine engine of claim 14 , wherein the first profiled region includes a lower most surface located in a forward 30% of the axial chord.

16. The gas turbine engine of claim 12 , wherein the second profiled region extends along approximately a forward 30% of the axial chord and extends along approximately 30% of the pitch between the first airfoil and the second airfoil.

17. The gas turbine engine of claim 12 , including a fourth profiled region protruding from the endwall along the second side of the second airfoil downstream from the third profiled region.

18. The gas turbine engine of claim 17 , including a fifth profiled region protruding from the endwall along the first side of the first airfoil upstream of the first profiled region.

19. The gas turbine engine of claim 18 , wherein the fourth profiled region extends along approximately an aft 50% axial chord and extends along approximately 50% of the pitch between the first airfoil and the second airfoil.

20. The gas turbine engine of claim 19 , wherein the fifth profiled region extends along approximately a forward 10% of the axial chord and extends along approximately 10% of the pitch between the first airfoil and the second airfoil.

Assignees

• United Technologies Corp

Inventors

• Nash Timothy Charles
• Ramirez Loubriel

Classifications

• F04D29/68

  by influencing boundary layers {(by bleeding elastic fluid F04D27/0215)} · CPC title

• F01D5/143 Primary

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F04D29/522

  especially adapted for elastic fluid pumps · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title