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US 7,452,189 B2Granted
Ceramic matrix composite turbine engine vane
AssigneeUnited Technologies Corporation
InventorsJun Shi, Stuart S. Ochs, Kevin E. Green, David C. Jarmon, Michael K. Sahm, Lisa A. Prill
Life of this patent
Estimating the term…
Abstract
A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The spar has a first chamber essentially along the suction side and a second chamber along the pressure side opposite the first chamber.
Claims20
A vane comprising:
- an airfoil shell comprising a ceramic matrix composite and having:
- a leading edge;
- a trailing edge;
- a pressure side;
- and
- a suction side;
- a metallic spar within the shell;
- an outboard shroud at an outboard end of the shell;
- and
- an inboard platform at an inboard end of the shell,
- wherein the spar comprises:
- a first chamber essentially along the suction side;
- and
- a second chamber along the pressure side opposite the first chamber.
11 more elements
A vane comprising:
- an airfoil shell having:
- a leading edge;
- a trailing edge;
- a pressure side;
- and
- a suction side;
- a spar within the shell;
- an outboard shroud at an outboard end of the shell;
- and
- an inboard platform at an inboard end of the shell,
- wherein the spar comprises:
- multi-chamber means in the spar for limiting thermal mechanical stress on the shell.
9 more elements
A method for engineering a vane having:
- an airfoil shell having:
- a leading edge;
- a trailing edge;
- a pressure side;
- and
- a suction side;
- a spar within the shell;
- an outboard shroud at an outboard end of the shell;
- and
- an inboard platform at an inboard end of the shell,
- the method comprising:
- configuring a plurality of chambers within the spar to provide airflow to cavities between the spar and shell so as to provide a desired internal pressure distribution within the shell.
9 more elements
Dependencies are inferred from the claim text.