Guide vane for a turbomachine, guide vane cascade, and method for manufacturing a guide vane or a guide vane cascade

Patent metadata

Field	Value
Publication number	US-9617865-B2
Application number	US-201414242152-A
Country	US
Kind code	B2
Filing date	Apr 1, 2014
Priority date	Apr 2, 2013
Publication date	Apr 11, 2017
Grant date	Apr 11, 2017

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.

First claim

What is claimed is:

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

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 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.

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.

Assignees

• MTU Aero Engines AG

Inventors

• Zotz Georg

Classifications

• F01D11/10 Primary

  using sealing fluid, e.g. steam · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• F04D29/164

  of an axial flow wheel · CPC title

• F01D5/18

  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 title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic