Turbine blade or vane with separate endwall

• US 8,961,134 B2
• Filed: 06/29/2011
• Issued: 02/24/2015
• Est. Priority Date: 06/29/2011
• Status: Expired due to Fees

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Beeck, Alexander R.
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): PRAGER, JESSE M
• Application Number:
  US13/171,678
• Publication Number:
  US 20130004331A1
• Time in Patent Office: 1,336 Days
• Field of Search: 416/97.R, 416/193.A, 416/96.A, 416/97.A, 416/224, 416/241.R, 416/243, 416/248, 415/115, 415/191, 415/914
• US Class Current: 416/97.R
• 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 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• 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 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades

Abstract

A turbine engine airfoil structure including an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine. The airfoil structure further includes a platform structure located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. The platform structure includes a platform member including a gas side surface extending generally perpendicular from the airfoil at a junction with the airfoil, and providing a structural connection to the airfoil. The platform structure further includes a separately formed platform cover attached to the platform member at the gas side surface. The platform cover extends from a location adjacent to one of the sidewalls of the airfoil, and includes an outer surface located for contact with the hot working gas passing through the gas path.

Claims

1. A turbine engine airfoil structure comprising:

an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine, the airfoil including sidewalls comprising radially extending pressure and suction sides;

a platform structure located at one end of the airfoil and positioned at a location forming a boundary of the gas passage, and including;

a platform member including a gas side surface extending generally perpendicular from the airfoil at a junction with the airfoil, and providing a structural connection to the airfoil; and

a separately formed platform cover attached to the platform member at the gas side surface, the platform cover including an outer surface located for contact with the hot working gas passing through the gas path, the outer surface comprising a contoured endwall surface having a first edge located adjacent to one of the sidewalls, wherein the platform cover includes a cooling fluid channel defined between the gas side surface of the platform member and a channel wall formed on the platform cover, the channel wall facing toward the gas side surface, wherein the channel wall comprises a plurality of support members extending from the channel wall and having distal end portions engaged on the platform member for retaining the platform cover to the platform member,

wherein the platform cover further comprises a second edge opposite the first edge and located generally aligned with a mateface of the platform member, the second edge being spaced from the mateface of the platform member to define a seal slot therebetween for receiving a mateface seal.

2. The airfoil structure of claim 1, wherein the contoured endwall surface includes a contour comprising at least one of an elevated ridge and a depressed trough.

3. The airfoil structure of claim 1, wherein the first edge is located in engagement with the sidewall and the contoured surface is located adjacent to a fillet joint formed between the airfoil and the platform member, the contoured surface providing a varying contour adjacent to the sidewall and extending in an axial direction between a leading edge and a trailing edge of the airfoil.

4. The airfoil structure of claim 1, including cooling structure formed on a side of the platform cover opposite the outer surface, the cooling structure comprising one or more cooling fluid channels for providing cooling across the gas side surface.

5. The airfoil structure of claim 4, including a cooling fluid passage having an outlet opening at the gas side surface for providing a cooling fluid to the one or more cooling fluid channels.

6. The airfoil structure of claim 1, wherein the platform cover substantially isolates the gas side surface from the hot working gas.

7. The airfoil structure of claim 1, wherein an intersection between the platform cover and the airfoil forms a sharp angle between the outer surface of the platform cover and the sidewall of the airfoil, the sharp angle being defined by an acute angle between the outer surface of the platform cover and the sidewall of the airfoil.

9. The airfoil structure of claim 1, wherein the support members are attached to the platform member at a welded connection.

10. The airfoil structure of claim 1, wherein the platform member includes recesses for receiving the distal end portions of the support members, the recesses including a form for capturing the distal end portions and preventing movement of the platform cover in a direction generally perpendicular to the gas side surface of the platform member.

11. The airfoil structure of claim 1, wherein the platform cover is formed of a material that is different from the material of the platform member.

8. A turbine engine airfoil structure comprising:

an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine, the airfoil including sidewalls comprising radially extending pressure and suction sides;

a platform structure located at one end of the airfoil and positioned at a location forming a boundary of the gas passage, and including;

a platform member including a gas side surface extending generally perpendicular from the airfoil at a junction with the airfoil, and providing a structural connection to the airfoil; and

a separately formed platform cover attached to the platform member at the gas side surface, the platform cover extending from a location radially displaced from the gas side surface and in contact with one of the sidewalls of the airfoil, and including an outer surface located for contact with the hot working gas passing through the gas path,

wherein the platform member includes a side edge defining a mateface and the platform cover includes a side edge defining a mateface, and including a slot defined between the gas side surface and the platform cover at the matefaces for receiving a seal member for forming a seal between the platform member and an adjoining platform member.