GUIDE VANE SYSTEM FOR A TURBOMACHINE

• US 20170226887A1
• Filed: 01/27/2017
• Published: 08/10/2017
• Est. Priority Date: 02/05/2016
• Status: Active Grant

• Current Assignee: MTU Aero Engines AG (MTU)
• Original Assignee: MTU Aero Engines AG (MTU)
• Inventors: WULF, Joachim, STIEHLER, Frank
• Granted Patent: US 10,450,888 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 11/003 by packing rings; Mechanical seals
• 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 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2260/36 by a form fit connection, e.g. by interlocking

Abstract

The invention relates to a guide vane system for a turbomachine with at least one guide vane, which can be rotatably mounted around an adjustment axis and is arranged with a radially inner end region in a corresponding recess of an inner ring, wherein the arrangement of the guide vane on the inner ring is secured by a securing element in a form-fitting manner. For an especially advantageous securing of this arrangement, it is provided that the securing element is designed as an oblong element, which is arranged at least in a recess and/or through-opening of the radially inner end region of the guide vane directed in the peripheral direction of the turbomachine and is arranged at least in a recess and/or through-opening of the inner ring directed in the peripheral direction of the turbomachine. In addition, the invention relates to a turbomachine, in particular an aircraft engine, and to a method for assembling a guide vane system.

Claims

1. A guide vane system (10) for a turbomachine with at least one guide vane (14), which is rotatably mounted around an adjustment axis (12) and is arranged with a radially inner end region (16) in a corresponding recess (18) of an inner ring (20, wherein the arrangement of the guide vane (14) on the inner ring (20) is secured by a securing element (22) in a form-fitting manner,

wherein

the securing element (22) is an oblong element, which is arranged at least in a recess (42) and/or through-opening (38) of the radially inner end region (16) of the guide vane (14) directed in the peripheral direction of the turbomachine and is arranged at least in a recess and/or through-opening (40) of the inner ring (20) directed in the peripheral direction of the turbomachine.

2. The guide vane system (10) according to claim 1, wherein

at least two guide vanes (14) of the guide vane system (10) are secured by a common securing element (22).

3. The guide vane system (10) according to claim 1, wherein

the recess (42) of the guide vane (14) is formed as a groove that runs on the outside at least partially around the radially inner end region (16) of the guide vane (14).

4. The guide vane system (10) according to claim 1, wherein

the securing element (22) is a securing wire that is round or square in cross section and runs in the peripheral direction.

5. The guide vane system (10) according to claim 1, wherein

the inner ring (20) is undivided in the axial direction of the turbomachine.

6. The guide vane system (10) according to claim 1, wherein

the inner ring (20) is divided into at least two inner ring segments (44) in the peripheral direction of the turbomachine.

7. The guide vane system (10) according to claim 6, wherein

one securing element (22) is provided for each inner ring segment (44).

8. The guide vane system (10) according to claim 1, wherein

the inner ring (20) is produced at least partially by an additive manufacturing method.

9. The guide vane system (10) according to claim 1, wherein

at least one sealing element (36) is arranged at the inner ring (20) radially on the inner side.

10. The guide vane system (10) according to claim 1, wherein

the recess (42) and/or the through-opening (38) of the radially inner end region (16) of the guide vane (14) have or has an oblong form, at least in sections, corresponding to the securing element (22), and/or the recess and/or the through-opening (40) of the inner ring (20) has an oblong form, at least in sections, corresponding to the securing element (22).

11. The guide vane system (10) according to claim 1, wherein the guide vane system is configured and arranged in an aircraft engine.

12. A method for assembling a guide vane system (10) for a turbomachine, comprising the steps of:

providing at least one a guide vane (14) that can be rotatably mounted around an adjustment axis (12) and that has a radially inner end region (16) having at least one recess (42) and/or through-opening (38) directed, in the installed position of the guide vane (14), in the peripheral direction of the turbomachine, providing an inner ring (26) with a recess (18) corresponding to the radially inner end region (16) of the guide vane (14) and with at least one recess and/or through-opening (40) directed in the peripheral direction of the turbomachine, and providing a securing element (22) formed as an oblong element;

inserting the radially inner end region (16) of the guide vane (14) into the recess (18) of the inner ring (20); and

inserting the securing element (22) into the recess (42) and/or into the through-opening (38) of the inner ring (20) and into the recess and/or into the through-opening (40) of the guide vane (14) for the form-fitting securing of the arrangement of the guide vane (14) on the inner ring (20).