Selectively coated gas path surfaces within a hot section of a gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorsEric Durocher, Ian MacFarlane, Guy Lefebvre
Life of this patent
Estimating the term…
Abstract
An apparatus is provided for a gas turbine engine. This gas turbine engine apparatus includes a hot section structure of the gas turbine engine. The hot section structure is configured with a plurality of surfaces respectively forming boundaries of a gas path through the hot section structure. The surfaces include a first surface and a second surface. The hot section structure includes metal and thermal barrier material. The first surface is formed by the metal. The second surface is formed by the thermal barrier material.
Claims20
An apparatus for a gas turbine engine, comprising:
- a hot section structure of the gas turbine engine;
- the hot section structure configured with a plurality of surfaces respectively forming boundaries of a gas path through the hot section structure, the plurality of surfaces including a first surface and a second surface;
- and
- the hot section structure including metal and thermal barrier material, the first surface formed by the metal, and the second surface formed by the thermal barrier material.
An apparatus for a gas turbine engine, comprising:
- a gas path wall forming a peripheral boundary of a gas path within the gas turbine engine;
- the gas path wall including a metal body and a thermal barrier coating disposed on the metal body, the metal body forming and exposed to the gas path along a first portion of the peripheral boundary, and the thermal barrier coating forming and exposed to the gas path along a second portion of the peripheral boundary.
An apparatus for a gas turbine engine, comprising:
- a first platform extending axially along and circumferentially about a centerline;
- a second platform extending axially along and circumferentially about the centerline;
- and
- a plurality of vanes arranged circumferentially about the centerline, each of the plurality of vanes extending radially between and connected to the first platform and the second platform, and the plurality of vanes comprising a first vane;
- wherein the first vane is configured with a thermal barrier coating, and at least a portion of the first platform adjacent the first vane is configured without a thermal barrier coating.
Dependencies are inferred from the claim text.