GUIDE VANE SEGMENT FOR A TURBOMACHINE

• US 20170159465A1
• Filed: 12/02/2016
• Published: 06/08/2017
• Est. Priority Date: 12/04/2015
• Status: Active Grant

• Current Assignee: MTU Aero Engines AG (MTU)
• Original Assignee: MTU Aero Engines AG (MTU)
• Inventors: Pernleitner, Martin, Mahle, Inga, Schlemmer, Markus, Wolfrum, Nina, Brettschneider, Markus
• Granted Patent: US 10,436,044 B2
• Time in Patent Office: Days
• 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 5/16 for counteracting blade vibration
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• 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

The invention relates to a guide vane cluster (10) for a turbomachine, in particular for a turbojet engine, having at least two vanes (14) that are joined together by way of at least one common platform (12, 16) for the radial delimiting of a flow channel of the turbomachine, wherein each vane (14) has a vane element (17) with a suction side (18) and a pressure side (20) that are joined together by a leading edge (22) and a trailing edge (24), wherein the at least two vanes (14) have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.

Claims

1. A guide vane cluster (10) for a turbomachine, having at least two vanes (14) that are joined together by way of at least one common platform (12, 16) for the radial delimiting of a flow channel of the turbomachine, wherein each vane (14) has a vane element (17) with a suction side (18) and a pressure side (20) that are joined together by a leading edge (22) and a trailing edge (24), wherein the at least two vanes (14) have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.

2. The guide vane cluster (10) according to claim 1, wherein at least two, and preferably all, vanes (14) are essentially designed identically, with the exception of their respective trailing edge regions.

3. The guide vane cluster (10) according to claim 1, wherein the at least two vanes (14) are joined together by way of a common radially inner platform (12) and a common radially outer platform (16).

4. The guide vane cluster (10) according to claim 1, wherein at least two vanes (14) have roundings with different rounding radii in their corresponding connection regions (26) to the at least one common platform (12, 16).

5. The guide vane cluster (10) according to claim 1, wherein it comprises at least three vanes (14), wherein at least two, and preferably all, vanes (14) have different trailing edge wall thicknesses in a corresponding radial lengthwise extension region.

6. The guide vane cluster (10) according to claim 1, wherein vanes (14) have at least one region in the vicinity of the platform that extends away from the platform (12, 16) by at most 25% of the radial lengthwise extension of the trailing edge (24), and/or have at least one region remote from the platform that extends by at least 25% of the radial lengthwise extension of the trailing edge (24) in a central region of the trailing edge (24).

7. The guide vane cluster (10) according to claim 6, wherein at least one of vanes (14) has a maximum trailing edge wall thickness in a region in the vicinity of the platform and/or in a region remote from the platform.

8. The guide vane cluster (10) according to claim 1, wherein the maximum and/or a minimum trailing edge wall thickness of at least one vane (14) is constant, at least essentially, along a predetermined radial lengthwise extension region.

9. The guide vane cluster (10) according to claim 1, wherein at least one vane (14) has a radial transition region between a maximum and a minimum trailing edge wall thickness.

10. The guide vane cluster (10) according to claim 9, wherein the trailing edge wall thickness in the transition region of vane (14) increases continually and/or monotonically from the minimum to the maximum trailing edge wall thickness, and/or that the transition region extends over at most 25% of the radial lengthwise extension of trailing edge (24).

11. The guide vane cluster (10) according to claim 1, wherein at least two vanes (14) have the same axial length and/or the same chord length and/or that at least one vane (14), when compared to at least one other vane (14), has a cut-back profile in the region of its trailing edge (24).

12. The guide vane cluster (10) according to claim 1, wherein at least one guide vane cluster is configured and arranged into a guide vane ring for a turbomachine.

13. The guide vane cluster (10) according to claim 12, wherein at least one guide vane cluster and/or at least one guide vane ring is configured and arranged into a turbojet engine.