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US 9,175,572 B2Granted
Turbomachine blade mounting system
AssigneeGeneral Electric Company
InventorsTimothy Scott McMurray, Thomas Joseph Farineau
Life of this patent
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Abstract
Embodiments of the present disclosure include a system having a turbine blade segment having a blade and a mounting segment coupled to the blade, wherein the mounting segment has a multi-piece assembly configured to mount in a radial direction into a slot of a turbomachine rotor.
Claims6
A system, comprising:
- a turbomachine rotor comprising a slot;
- and
- a turbomachine blade mounting segment having first and second configurations, wherein the first configuration is configured to tangentially insert in a radial direction into the slot of the turbomachine rotor, and the second configuration is configured to expand relative to the first configuration to retain the turbomachine blade mounting segment in the slot, wherein the turbomachine blade mounting segment comprises a first dovetail segment, a second dovetail segment, a captured spreader piece, and a cover portion having a retention feature, the cover portion is configured to couple the first dovetail segment, the second dovetail segment, and the captured spreader piece to one another, and the first dovetail segment, the second dovetail segment, and the captured spreader piece are each configured to be individually inserted in the radial direction into the slot, and at least one portion of the turbomachine blade mounting segment is integrally formed with a turbomachine blade configured to be coupled to the turbomachine rotor by the turbomachine blade mounting segment.
A system, comprising:
- a first turbomachine blade mounting segment configured to couple only a first turbomachine blade to a turbomachine rotor;
- and
- a second turbomachine blade mounting segment configured to couple only a second turbomachine blade to the turbomachine rotor,
- wherein the first and second turbomachine blade mounting segments are configured to tangentially insert in a radial direction into a slot of the turbomachine rotor, and then expand in the slot, wherein the second turbomachine blade mounting segment comprises a first dovetail segment, a second dovetail segment, a spreader piece, and a cover portion having a retention feature, wherein the cover portion is configured to couple the first dovetail segment, the second dovetail segment, and the spreader piece to one another, wherein the first dovetail segment, the second dovetail segment, and the spreader piece are individually insertable in the radial direction into the slot of the turbomachine rotor to expand the second turbomachine blade mounting segment in the slot.
1 more element
Dependencies are inferred from the claim text.