Endwall Contouring for Airfoil Rows With Varying Airfoil Geometries

• US 20160076392A1
• Filed: 08/03/2015
• Published: 03/17/2016
• Est. Priority Date: 09/12/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Thomas, Flavien L.
• Granted Patent: US 10,151,210 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 11/008 by spacer elements between the blades, e.g. independent interblade platforms
• CPC Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F01D 5/143 Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• CPC Class Codes: F01D 5/147 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 Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: F04D 29/545 Ducts
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2240/24 for turbines
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: F05D 2260/961 by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An airfoil array for a gas turbine engine comprises a plurality of airfoils spaced circumferentially apart from each other about an engine center axis. Each airfoil is associated with a platform. An endwall extends circumferentially about the engine center axis, and is defined by adjacent platforms. Each pair of adjacent platforms are separated from each other by a gap. An endwall contour shape extends from a first location on one side of the gap to a second location on an opposite of the gap. The endwall contour shape is the same for all adjacent platforms. A gas turbine engine and a method of forming an airfoil array for a gas turbine engine are also disclosed.

Claims

1. An airfoil array for a gas turbine engine comprising:

a plurality of airfoils spaced circumferentially apart from each other about an engine center axis, each airfoil being associated with a platform;

an endwall extending circumferentially about the engine center axis, the endwall being defined by adjacent platforms, and wherein each pair of adjacent platforms are separated from each other by a gap; and

an endwall contour shape defined to extend from a first location on one side of the gap to a second location on an opposite of the gap, and wherein the endwall contour shape is the same for all adjacent platforms.

2. The airfoil array according to claim 1, wherein the plurality of airfoils includes at least a first airfoil type and a second airfoil type that is different than the first airfoil type.

3. The airfoil array according to claim 2, wherein the plurality of airfoils includes a pair of first airfoil types that are adjacent to each other with each first airfoil type having a first platform type, and wherein the endwall contour shape comprises a first endwall contour shape that is defined by a first portion extending from the first location on one of the first platform types to the gap and a second portion extending from the opposite side of the gap to the second location on the other of the first platform types, and including a first additional endwall contour extending from the first location to a first area adjacent to the airfoil associated with the one of the first platform types and a second additional endwall contour extending from the second location to a second area adjacent to the airfoil associated with the other of the first platform types.

4. The airfoil array according to claim 3, wherein the plurality of airfoils includes a pair of second airfoil types that are adjacent to each other with each second airfoil type having a second platform type, and wherein the endwall contour shape further comprises a second endwall contour shape that is defined by a first portion extending from the first location on one of the second platform types to the gap and a second portion extending from the opposite side of the gap to the second location on the other of the second platform types, and including a third additional endwall contour extending from the first location to a third area adjacent to the airfoil associated with the one of the second platform types and a fourth additional endwall contour extending from the second location to a fourth area adjacent to the airfoil associated with the other of the second platform types, and wherein the second endwall contour shape is identical to the first endwall contour shape.

5. The airfoil array according to claim 4, wherein the first additional endwall contour is different than the second additional endwall contour.

6. The airfoil array according to claim 4, wherein the third additional endwall contour is different than the fourth additional endwall contour.

7. The airfoil array according to claim 4, wherein the first and second additional endwall contours are different than the third and fourth additional endwall contours.

8. The airfoil array according to claim 4, wherein the plurality of airfoils includes a first airfoil type adjacent to a second airfoil type, and wherein the endwall contour shape further comprises a third endwall contour shape that is defined by a first portion extending from the first location on the first platform type to the gap and a second portion extending from the opposite side of the gap to the second location on the second platform type, and including a fifth additional endwall contour extending from the first location to a fifth area adjacent to the airfoil associated with the first platform type and a sixth additional endwall contour extending from the second location to a sixth area adjacent to the airfoil associated with the second platform type, and wherein the third endwall contour shape is identical to the first and second endwall contour shapes.

9. The airfoil array according to claim 1, wherein the endwall contour shape defines a first endwall portion, and wherein the first location is on a first platform with a first airfoil and the second location is on a second platform with a second airfoil, and wherein the first location is circumferentially spaced apart from a side of the first airfoil by a first distance that defines a second endwall portion, and wherein the second location is circumferentially spaced apart from a side of the second airfoil by a second distance to form a third end wall portion such that an endwall segment extending from the first airfoil to the second endwall is entirely defined by the first, second, and third endwall portions.

10. The airfoil array according to claim 9, wherein the first and second airfoils are different types from each other or are the same type as each other, and wherein the first end wall portion is the same when the first and second airfoils are different from, or the same as, each other.

11. A gas turbine engine comprising:

a compressor section;

a combustor section downstream of the compressor section; and

a turbine section downstream of the combustor section, and wherein at least one of the combustor section, the turbine section, or a fan exit guide vane section, include an airfoil array that is comprised of

a plurality of airfoils spaced circumferentially apart from each other about an engine center axis, each airfoil being associated with a platform,

an endwall extending circumferentially about the engine center axis, the endwall being defined by adjacent platforms, and wherein each pair of adjacent platforms are separated from each other by a gap, and

wherein the plurality of airfoils includes at least a first airfoil on a first platform and a second airfoil on a second platform with the first and second platforms being separated from each other by the gap; and

an endwall contour shape defined to extend from a first location on the first platform to a second location on the second platform, and wherein the endwall contour shape is the same for all adjacent platforms.

12. The gas turbine engine according to claim 11, wherein an endwall segment is defined as extending from one side of the first airfoil and across the gap to a side of the second airfoil that faces the first airfoil, and wherein the endwall contour shape defines a first endwall portion of the endwall segment, and wherein the first location is circumferentially spaced apart from the side of the first airfoil by a first distance that defines a second endwall portion, and wherein the second location is circumferentially spaced apart from the side of the second airfoil by a second distance to form a third end wall portion such that the endwall segment is entirely defined by the first, second, and third endwall portions.

13. The gas turbine engine according to claim 12, wherein the first and second airfoils are different types from each other or are the same type as each other, and wherein the first end wall portion is the same if the first and second airfoils are different from each other or if the first and second airfoils are the same as each other.

14. The gas turbine engine according to claim 13, wherein the second and third endwall portions are different from the first end wall portion.

15. The gas turbine engine according to claim 13, wherein the second and third endwall portions are different from each other.

16. A method of forming an airfoil array for a gas turbine engine comprising the steps of:

spacing a plurality of airfoils circumferentially apart from each other about an engine center axis, each airfoil being associated with a platform;

forming an endwall that extends circumferentially about the engine center axis, the endwall being defined by adjacent platforms, and wherein each pair of adjacent platforms are separated from each other by a gap;

wherein the plurality of airfoils includes at least a first airfoil on a first platform and a second airfoil on a second platform with the first and second platforms being separated from each other by the gap; and

shaping an endwall contour to extend from a first location on the first platform to a second location on the second platform, wherein the endwall contour is shaped to be the same for all adjacent platforms regardless of airfoil type.

17. The method according to claim 16 including

defining an endwall segment as extending from one side of the first airfoil, across the gap, and to a side of the second airfoil that faces the first airfoil,

defining the endwall contour to comprise a first endwall portion of the endwall segment,

spacing the first location circumferentially apart from the side of the first airfoil by a first distance that defines a second endwall portion, and

spacing the second location circumferentially apart from the side of the second airfoil by a second distance to form a third end wall portion such that the endwall segment is entirely defined by the first, second, and third endwall portions.

18. The method according to claim 17, wherein the first and second airfoils are different types from each other or are the same type as each other, and wherein the first end wall portion is the same if the first and second airfoils are different from each other or if the first and second airfoils are the same as each other.

19. The method according to claim 18, wherein the first and second airfoils are different types from each other, and including blending a first transition from the first location to match a platform profile for the first airfoil type to form the second endwall portion, and blending a second transition from the second location to match a platform profile for the second airfoil type to form the third endwall portion.

20. The method according to claim 17, wherein the second and third endwall portions are different from the first end wall portion, and are different from each other.