Axial compressor integrated bladed rotor airfoil design scheme
AssigneePratt & Whitney Canada Corp.
InventorsChao Zhang, Rambod Larijani
Life of this patent
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Abstract
An integrally bladed rotor (IBR) includes a hub and blades, each blade includes an airfoil section extending from a blade root at the hub to a blade tip defining a radially outboard extent of the rotor blade to aerodynamically interact with a flow of air for compressing the air. A root fillet is integrally formed with the hub the airfoil section integrally extends therefrom. The blade includes a localized increased blade root thickness portion defined based on at least one of an axial thickness of a web portion of the hub and a chord length of the blade.
Claims20
An integrally bladed rotor (IBR), comprising:
- a hub;
- and
- blades, each blade comprising:
- an airfoil section extending from a blade root at the hub to a blade tip defining a radially outboard extent of the rotor blade to aerodynamically interact with a flow of air for compressing the air;
- and
- a root fillet integrally formed with the hub and from which the airfoil section integrally extends;
- wherein the blade includes a localized increased blade root thickness portion having a maximum axial length and a maximum percentage increase in blade thickness defined as a function of an axial thickness of the hub.
A compressor assembly of a gas turbine engine, comprising one or more compressor rotors arrayed along an engine central longitudinal axis, at least one compressor rotor of the one or more compressor rotors comprising an integrally bladed rotor (IBR) including:
- a hub;
- and
- blades, each blade comprising:
- an airfoil section extending from a blade root at the hub to a blade tip defining a radially outboard extent of the rotor blade to aerodynamically interact with a flow of air for compressing the air;
- and
- a root fillet integrally formed with the hub and from which the airfoil section integrally extends;
- wherein the blade includes a localized increased blade root thickness portion having a maximum axial length and a maximum percentage increase in blade thickness defined as a function of an axial thickness of the hub.
A gas turbine engine, comprising:
- a turbine driven by products of a combustor;
- and
- a compressor operably connected to the turbine and driven by rotation of the turbine, the compressor including an integrally bladed rotor (IBR), the IBR including:
- a hub;
- and
- blades, each blade comprising:
- an airfoil section extending from a blade root at the hub to a blade tip defining a radially outboard extent of the rotor blade to aerodynamically interact with a flow of air for compressing the air;
- and
- a root fillet integrally formed with the hub and from which the airfoil section integrally extends;
- wherein the blade includes a localized increased blade root thickness portion having a maximum axial length and a maximum percentage increase in blade thickness defined as a function of an axial thickness of the hub.
Dependencies are inferred from the claim text.