ROTOR FOR A TURBOMACHINE
First Claim
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.
1 Assignment
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Accused Products
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.
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Citations
13 Claims
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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. - View Dependent Claims (2, 3, 4, 6, 7, 8, 9)
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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.
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10. A method for manufacturing a blade ring of a rotor for a turbomachine including the following steps:
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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. - View Dependent Claims (11, 12, 13)
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Specification