Rotor for a turbomachine

Patent metadata

Field	Value
Publication number	US-9657581-B2
Application number	US-201313746650-A
Country	US
Kind code	B2
Filing date	Jan 22, 2013
Priority date	Jan 23, 2012
Publication date	May 23, 2017
Grant date	May 23, 2017

Abstract

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

First claim

What is claimed is:

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 blade 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 a first platform group edge, and an adjacent blade platform of the associated second group of rotor blades having a matching projection situated on a second platform group edge, arranged in a form-locked manner;
wherein each blade platform of the first group of rotor blades has the recess, situated on the first platform group edge, as well as an opposite projection, situated on the first platform group edge, wherein the opposite projection is located at an opposite side of the first platform group edge from the recess such that the opposite projection is spaced apart from the recess in the axial direction, wherein the axial direction is along an axis of rotation of the rotor, and each blade platform of the second group of rotor blades has the projection situated on the second platform group edge matching the recess of the blade platform of the first group and a further recess situated on the second platform group edge which matches the opposite projection,

wherein the projection is located at an opposite side of the second platform group edge from the further recess such that the projection is spaced apart from the further recess in the axial direction.

2. The rotor as recited in claim 1 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.

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

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

5. The rotor as recited in claim 4 wherein the contact surfaces have at least one of an oblique, wavy, serrated and irregular shape.

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

7. 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, wherein 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 a first platform group edge and in which a matching projection, situated on a second platform group 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;
wherein each blade platform of the first group of rotor blades has the recess, situated on the first platform group edge, as well as an opposite projection, situated on the first platform group edge, wherein the opposite projection is located at an opposite side of the first platform group edge from the recess such that the opposite projection is spaced apart from the recess in the axial direction, wherein the axial direction is along an axis of rotation of the rotor; and
wherein each blade platform of the second group of rotor blades has the projection situated on the second platform group edge matching the recess of the blade platform of the first group and a further recess situated on the second platform group edge which matches the opposite projection, wherein the projection is located at an opposite side of the second platform group edge from the further recess such that the projection is spaced apart from the further recess in the axial direction.

8. The method as recited in claim 7 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).

9. The method as recited in claim 8 wherein blade roots of the rotor blades are arranged and established in a matching groove of a rotor base body in step b).

10. The method as recited in claim 7 wherein at least two groups of rotor blades having different blade geometries are provided in step a).

11. A blade ring manufactured according to the method in claim 7 .

12. A jet engine comprising the blade ring as recited in claim 11 .

13. 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;
b) forming, via a separation process, a recess on an edge of each blade platform of a first group and a projection on an opposite side of the edge of each blade platform of the first group, such that the recess and the projection are spaced apart in the axial direction, wherein the axial direction is along an axis of rotation of the rotor;
c) forming, via a separation process, a matching projection on an edge of each blade platform of a second group and a matching recess on an opposite side of the edge of each blade platform of the second group, such that the recess and the projection are spaced apart in the axial direction, and such that each blade platform 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
d) 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, wherein each blade platform of the first group of the at least two groups of the rotor blades having the recess and the projection which is situated on the edge and in which the matching projection and the matching recess, situated on the edge of an adjacent blade platform of the second group of the at least two groups of the rotor blades, respectively, is arranged in a form-locked manner.

14. The method as recited in claim 13 wherein the separation process includes at least one of milling and grinding.

Assignees

• Mtu Aero Engines Gmbh

Inventors

• Woehler Marcus
• Pernleitner Martin
• Stanka Rudolf

Classifications

• F01D5/3007

  of axial insertion type · CPC title

• F01D25/06

  for preventing blade vibration (means on blade-carrying members or blades F01D5/00) · CPC title

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• Y10T29/4932

  Turbomachine making · CPC title