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US 10,590,780 B2Granted
Engine component having support with intermediate layer
AssigneeUnited Technologies Corporation
InventorMichael G. McCaffrey
Life of this patent
Estimating the term…
Abstract
Disclosed is a gas turbine engine component, and a method for forming the component. The component includes a first portion, a second portion formed separately from the first portion, and an intermediate layer provided between the first portion and the second portion.
Claims18
A gas turbine engine, comprising:
- a compressor section, a combustor section, and a turbine section, the turbine section including a stationary stage and a rotating stage;
- a component provided in one of the stationary stage and the rotating stage, the component including a first portion, wherein the first portion includes an airfoil section and a root of a turbine blade, a second portion formed separately from the first portion and at least partially disposed radially outward of a rotor disc of the turbine section, and an intermediate layer provided between the first portion and the second portion, wherein, in an initial condition before any wear or de-bonding of the intermediate layer, the first portion abuts the second portion indirectly via the intermediate layer at a location, and wherein, after the initial condition, the intermediate layer wears and becomes de-bonded from the first portion at least at the location such that the first portion directly abuts the second portion at the location.
A gas turbine engine component, comprising:
- a first portion, wherein the first portion includes an airfoil section and a root of a turbine blade;
- a second portion formed separately from the first portion, wherein the second portion includes a platform of the turbine blade, the second portion at least partially disposed radially outward of a rotor disc of a turbine section;
- and
- an intermediate layer provided between the first portion and the second portion, wherein, in an initial condition before any wear or de-bonding of the intermediate layer, the first portion abuts the second portion indirectly via the intermediate layer at a location, and wherein, after the initial condition, the intermediate layer wears and becomes de-bonded from the first portion at least at the location such that the first portion directly abuts the second portion at the location.
1 more element
A method of forming a component for a gas turbine engine comprising:
- forming a first portion of the component;
- providing an intermediate layer over the component;
- and
- forming a second portion of the component over the intermediate layer, wherein the first portion of the component includes an airfoil section and a root of a turbine blade, and the second portion of the component is a supporting structure configured to support the first portion and includes a platform, the second portion at least partially disposed radially outward of a rotor disc of a turbine section, and wherein, in an initial condition before any wear or de-bonding of the intermediate layer, the first portion abuts the second portion indirectly via the intermediate layer at a location, and wherein, after the initial condition, the intermediate layer wears and becomes de-bonded from the first portion at least at the location such that the first portion directly abuts the second portion at the location.
1 more element
A gas turbine engine, comprising:
- a compressor section, a combustor section, and a turbine section, the turbine section including a stationary stage and a rotating stage;
- a component provided in one of the stationary stage and the rotating stage, the component including a first portion, a second portion formed separately from the first portion, and an intermediate layer provided between the first portion and the second portion, wherein the intermediate layer wears and becomes at least partially de-bonded from the first portion during operation of the gas turbine engine, and
- wherein the intermediate layer becomes completely worn away during operation of the gas turbine engine.
Dependencies are inferred from the claim text.