ROTOR FOR A TURBOMACHINE

• US 20130189111A1
• Filed: 01/22/2013
• Published: 07/25/2013
• Est. Priority Date: 01/23/2012
• Status: Active Grant

• Current Assignee: MTU Aero Engines GmbH (MTU)
• Original Assignee: MTU Aero Engines GmbH (MTU)
• Inventors: Stanka, Rudolf, Woehler, Marcus, Pernleitner, Martin
• Granted Patent: US 9,657,581 B2
• Time in Patent Office: Days
• US Class Current: 416/220.R
• CPC Class Codes: F01D 25/06 for preventing blade vibration means on blade-carrying members or blades F01D5/00
• CPC Class Codes: F01D 5/26 Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
• CPC Class Codes: F01D 5/3007 of axial insertion type
• CPC Class Codes: F01D 5/3038 the slot having inwardly directed abutment faces on both sides
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2260/36 by a form fit connection, e.g. by interlocking
• CPC Class Codes: Y10T 29/4932 Turbomachine making

Abstract

A rotor for a turbomachine, in particular for a jet engine, having a blade ring which includes multiple differently designed rotor blades (10a, 10b) having blade platforms (14a, 14b) engaged flush with one another, the blade ring including at least two groups of differently designed rotor blades (10a, 10b), each group of rotor blades (10a, 10b) being assigned blade platforms (14a, 14b), each of which is engageable flush with a matching blade platform (14a, 14b) of at least one other group of rotor blades (10a, 10b) and not with a blade platform (14a, 14b) of the same group of rotor blades (10a, 10b). A method for manufacturing a blade ring of a rotor for a turbomachine as well as a jet engine.

Claims

1. A rotor for a turbomachine comprising:

a blade ring including at least a first group of rotor blades and a second group of rotor blades differently designed from the first group of rotor blades, the first group of rotor blades being assigned first blade platforms, each of which is engageable flush with a matching blade platform of the second group of rotor blades and not with another blade platform of the first group of rotor blades, the blade platforms of the second group of rotor blades also not being engageable flush with another blaed platform of the second group of rotor blades, each blade platform of the first group of rotor blades having at least one recess situated on an edge, and a matching projection, situated on another edge, of an adjacent blade platform of the associated second group of rotor blades, arranged in a form-locked manner.

2. The rotor as recited in claim 1 wherein the recess and/or the projection of the blade platforms of the first and second groups is/are introduced with the aid of a separation process.

3. The rotor as recited in claim 2 wherein the separation process includes at least one of milling and grinding.

4. The rotor as recited in claim 2 wherein each blade platform of the first group of rotor blades has the recess, situated on the edge, as well as an opposite projection, situated on the edge, and each blade platform of the second group of rotor blades has the projection situated on the other edge matching the recess of the blade platform of the first group and a further recess situated on the further edge which matches the opposite projection.

6. The rotor as recited in claim 1 wherein the first and second groups of rotor blades have different blade geometries.

7. The rotor as recited in claim 1 wherein the blade platforms of the first and second groups having matching lateral contact surfaces.

8. The rotor as recited in claim 7 wherein the contact surfaces have at least one of an oblique, wavy, serrated and irregular shape.

9. A jet engine comprising the rotor as recited in claim 1.

5. The rotor as recited in claim I wherein the recesses and the matching projections are designed in the area of the lateral contact surfaces of the rotor blades of the first and second groups, the projections being form-locked in their respective recesses.

10. A method for manufacturing a blade ring of a rotor for a turbomachine including the following steps:

a) providing at least two groups of differently designed rotor blades, each group of rotor blades being assigned blade platforms, each of which is engageable flush with a matching blade platform of at least one other group of rotor blades and not with a blade platform of the same group of rotor blades; and

b) arranging the rotor blades in the shape of the blade ring, each of the matching blade platforms of the at least two groups of rotor blades being engaged flush with one another,

each blade platform of a first group of the at least two groups of the rotor blades having at least one recess which is situated on the edge and in which a matching projection, situated on the edge, of an adjacent blade platform of an associated second group of the at least two groups of the rotor blades is arranged in a form-locked manner.

11. The method as recited in claim 10 wherein blade platforms of the first group of rotor blades and the blade platforms of the second group of rotor blades are alternatingly engaged in step b).

12. The method as recited in claim 11 wherein blade roots of the rotor blades are arranged and established in a matching groove of a rotor base body in step b).

13. The method as recited in claim 10 wherein at least two groups of rotor blades having different blade geometries are provided in step a).