Tip cap for a turbine rotor blade
Abstract
A turbine rotor blade with a spar and shell construction, and a tip cap that includes a row of lugs extending from a bottom side that form dovetail grooves that engage with similar shaped lugs and grooves on a tip end of the spar to secure the tip cap to the spar against radial displacement. The lug on the trailing edge end of the tip cap is aligned perpendicular to a chordwise line of the blade in the trailing edge region in order to minimize stress due to the lugs wanting to bend under high centrifugal loads. A two piece tip cap with lugs at different angles will reduce the bending stress even more.
- Inventors:
- Issue Date:
- Research Org.:
- Florida Turbine Technologies, Inc., Jupiter, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1128688
- Patent Number(s):
- 8678764
- Application Number:
- 12/606,463
- Assignee:
- Florida Turbine Technologies, Inc. (Jupiter, FL)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- DOE Contract Number:
- FG02-07ER84668
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2009 Oct 27
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Kimmel, Keith D. Tip cap for a turbine rotor blade. United States: N. p., 2014.
Web.
Kimmel, Keith D. Tip cap for a turbine rotor blade. United States.
Kimmel, Keith D. Tue .
"Tip cap for a turbine rotor blade". United States. https://www.osti.gov/servlets/purl/1128688.
@article{osti_1128688,
title = {Tip cap for a turbine rotor blade},
author = {Kimmel, Keith D},
abstractNote = {A turbine rotor blade with a spar and shell construction, and a tip cap that includes a row of lugs extending from a bottom side that form dovetail grooves that engage with similar shaped lugs and grooves on a tip end of the spar to secure the tip cap to the spar against radial displacement. The lug on the trailing edge end of the tip cap is aligned perpendicular to a chordwise line of the blade in the trailing edge region in order to minimize stress due to the lugs wanting to bend under high centrifugal loads. A two piece tip cap with lugs at different angles will reduce the bending stress even more.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Mar 25 00:00:00 EDT 2014},
month = {Tue Mar 25 00:00:00 EDT 2014}
}
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Works referenced in this record:
Rotor blade and stator vane using ceramic shell
patent, May 1985
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Method of making replacement airfoil components
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Leading edge configuration for compressor blades of gas turbine engines
patent, June 2010
- Schreiber, Karl; Heinrich, Roland
- US Patent Document 7,744,346
Gas-turbine blade featuring a modular design
patent, January 2012
- Gerakis, Jeffrey-George; Davison, Peter
- US Patent Document 8,100,653
Works referencing / citing this record:
Multiple piece turbine rotor blade
patent, July 2016
- Kimmel, Keith D.; Plank, William L.
- US Patent Document 9,394,795