Single crystal, environmentally-resistant gas turbine shroud
An uncoated, cast shroud segment is described for use in a gas turbine engine at temperatures up to at least 2,100 F, comprising a substantially single crystal microstructure which is solution treated and aged and having a composition, in weight percent, of from a bout 6.75 to about 7.25 percent chromium, from about 7.0 to about 8.0 percent cobalt, from about 1.3 to about 1.7 percent molybdenum, from about 4.75 to about 5.25 percent tungsten, from about 6.3 to about 6.7 percent tantalum, from about 0 to about 0.02 percent titanium, from about 6.1 to about 6.3 percent aluminum, from about 2.75 to about 3.25 percent rhenium, from about 0.12 to about 0.18 percent hafnium, from about 0.04 to about 0.06 percent carbon, from about 0.003 to about 0.005 percent boron, from about 0.002 to about 0.030 percent yttrium, balance nickel, wherein the uncoated shroud segment exhibits improved oxidation resistance at elevated temperatures, the improved oxidation resistance being measured by a weight loss of about 1.0 mil or less at a temperature of about 2,150 F. for a time of about 200 hours by a Mach 1 burner rig test.
- Assignee:
- General Electric Co., Cincinnati, OH (United States)
- Patent Number(s):
- US 5240518; A
- Application Number:
- PPN: US 7-577668
- OSTI ID:
- 5991220
- Resource Relation:
- Patent File Date: 5 Sep 1990
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
GAS TURBINE ENGINES
HEAT RESISTANT MATERIALS
ALUMINIUM ALLOYS
BORON ADDITIONS
CHROMIUM ALLOYS
COBALT ALLOYS
CORROSION RESISTANCE
HAFNIUM ADDITIONS
HEAT RESISTING ALLOYS
MICROSTRUCTURE
MOLYBDENUM ALLOYS
NICKEL ALLOYS
RHENIUM ALLOYS
TEMPERATURE RANGE 1000-4000 K
TITANIUM ADDITIONS
TUNGSTEN ALLOYS
YTTRIUM ADDITIONS
ALLOYS
BORON ALLOYS
ENGINES
HAFNIUM ALLOYS
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MATERIALS
TEMPERATURE RANGE
TITANIUM ALLOYS
YTTRIUM ALLOYS
330103* - Internal Combustion Engines- Turbine