GUIDE VANE FOR A TURBOMACHINE, GUIDE VANE CASCADE, AND METHOD FOR MANUFACTURING A GUIDE VANE OR A GUIDE VANE CASCADE

• US 20170175756A1
• Filed: 03/01/2017
• Published: 06/22/2017
• Est. Priority Date: 04/02/2013
• Status: Active Grant

• Current Assignee: MTU Aero Engines AG (MTU)
• Original Assignee: MTU Aero Engines AG (MTU)
• Inventors: Zotz, Georg
• Granted Patent: US 10,060,439 B2
• Time in Patent Office: Days
• CPC Class Codes: B22F 10/28 Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• CPC Class Codes: B22F 2998/10 Processes characterised by the sequence of their steps
• CPC Class Codes: B22F 5/04 of turbine blades
• CPC Class Codes: B23K 2101/001 Turbines
• CPC Class Codes: B23K 26/342 Build-up welding
• CPC Class Codes: B23P 15/04 turbine or like blades from several pieces
• CPC Class Codes: B33Y 10/00 Processes of additive manufacturing
• CPC Class Codes: B33Y 80/00 Products made by additive manufacturing
• CPC Class Codes: F01D 11/00 Preventing or minimising internal leakage of working-fluid, e.g. between stages sealings in general F16J ; sealing arrangements for transition ducts of combustor cans F01D9/023
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 11/10 using sealing fluid, e.g. steam
• CPC Class Codes: F01D 17/14 varying effective cross-sectional area of nozzles or guide conduits
• CPC Class Codes: F01D 17/16 by means of nozzle vanes
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• 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: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F04D 19/00 Axial-flow pumps F04D21/00 takes precedence; pump comprising axial flow and radial flow stages F04D17/025
• CPC Class Codes: F04D 29/164 of an axial flow wheel
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: F04D 29/56 adjustable
• CPC Class Codes: Y02P 10/25 : Process efficiency
• CPC Class Codes: Y02T 50/60 : Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49336 : Blade making

Abstract

A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade.

Claims

1. A guide vane for a turbomachine comprising:

an upper trailing edge and a lower trailing edge, the guide vane being axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine, a trailing edge gap being formed between the upper trailing edge of the guide vane and the flow-limiting wall or between the lower trailing edge of the guide vane and the inner ring,

wherein the upper trailing edge or the lower trailing edge of the guide vane has at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge or the trailing edge gap in the area of the lower trailing edge;

wherein the guide vane has a blade surface, the air outlet opening communicating air-conductively via at least one channel with at least one air inlet opening on the blade surface; and

wherein the air inlet opening is configured on an active surface of the guide vane.

2. The guide vane as recited in claim 1 wherein at least one localized thickened portion of the guide vane is formed in the area of the air inlet opening prior to the manufacture of the air inlet opening.

3. The guide vane as recited in claim 2 further comprising at least one air baffle in the area of the air inlet opening.

4. The guide vane as recited in claim 1 wherein the air outlet opening is configured to be funnel- or slit-shaped.

5. The guide vane as recited in claim 1 wherein the active surface is includes the pressure side of the guide vane.

6. A guide vane cascade of a turbomachine comprising at least two guide vanes as recited in claim 1.

7. A compressor or turbine of an aircraft engine comprising the guide vane cascade as recited in claim 6.

8. A compressor or turbine of an aircraft engine comprising the guide vane as recited in claim 1.

9. A method for manufacturing a guide vane as recited in claim 1 wherein the guide vane is manufactured using a generative production process.

10. The method as recited in claim 9 wherein the generative production process is a selective laser melting process or a selective laser sintering process.

11. A method for manufacturing a guide vane cascade as recited in claim 6 wherein the at least two guide vanes are manufactured using a generative production process.