Method for modifying gas turbine nozzle area
AssigneeHoneywell International Inc.
InventorsMark Morris, Thomas Strangman, Craig Wilson, George Wolfmeyer, Steve Halfmann, David Jan
Life of this patent
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Abstract
A method of modifying a turbine nozzle area comprises depositing a thermal barrier coating (TBC) on the nozzle endwalls to provide a minimum nozzle area, evaluating an airflow through the nozzle, and machining the TBC to increase the nozzle area. Adjacent segment area variation may be minimized, improving engine reliability by reducing the aerodynamic excitation to the down stream blade.
Claims38
A method of modifying a nozzle area for a turbine nozzle comprising the steps of:
- depositing a thermal barrier coating on at least one endwall of said turbine nozzle such that an initial nozzle area is produced;
- and
- modifying said thermal barrier coating such that said initial nozzle area is adjusted to provide a first nozzle area.
A method of modifying a nozzle area for a turbine nozzle comprising the steps of:
- depositing a first thermal barrier coating on a radially inward side of a nozzle outer endwall of said turbine nozzle;
- depositing a second thermal barrier coating on a radially outward side of a nozzle inner endwall of said turbine nozzle, such that an initial nozzle area is produced;
- and
- machining at least one of said first thermal barrier coating and said second thermal barrier coating such that said initial nozzle area is adjusted to provide a first nozzle area.
A method of modifying a nozzle area comprising the steps of:
- providing a turbine nozzle having a thermal barrier coating deposited on at least one endwall;
- and
- machining said thermal barrier coating such that said nozzle area is increased.
A method of modifying a nozzle area for a turbine nozzle comprising the step of:
- modifying a thermal barrier coating of at least one endwall of said turbine nozzle.
A method of modifying a nozzle area for a turbine nozzle comprising the steps of:
- depositing a first thermal barrier coating on a radially inward side of a nozzle outer endwall of said turbine nozzle, said step of depositing to a thickness between about 0.02 inches and about 0.10 inches, said thermal barrier coating selected from the group consisting of tetragonal zirconia stabilized with about 7% to about 8% by weight yttria and cubic zirconia stabilized with about 15% to about 30% by weight yttria;
- depositing a second thermal barrier coating on a radially outward side of a nozzle inner endwall of said turbine nozzle, said step of depositing to a thickness between about 0.02 inches and about 0.10 inches, said thermal barrier coating selected from the group consisting of tetragonal zirconia stabilized with about 7% to about 8% by weight yttria and cubic zirconia stabilized with about 15% to about 30% by weight yttria;
- brazing a radially outward end of at least one nozzle vane to said radially inward side;
- brazing a radially inward end of at least one nozzle vane to said radially outward side;
- and
- machining said first thermal barrier coating and said second thermal barrier coating such that an increased nozzle area is produced.
A turbine nozzle comprising:
- a nozzle inner endwall;
- a nozzle outer endwall positioned radially outward from said nozzle inner endwall, wherein at least one of said nozzle inner endwall and said nozzle outer endwall has a thermal barrier coating capable of being machined such that a nozzle area of said turbine nozzle is increased;
- and
- at least one nozzle vane positioned radially outward from said nozzle inner endwall and positioned radially inward from said nozzle outer endwall.
Dependencies are inferred from the claim text.