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US 11,143,038 B2Granted
Gas turbine engine high lift airfoil cooling in stagnation zone
AssigneeRaytheon Technologies Corporation
InventorsSan Quach, Matthew A. Devore
Life of this patent
Estimating the term…
Abstract
An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. A stagnation line is located on the pressure side wall aft of the leading edge. A cooling passage is provided between the pressure and suction side walls. Forward-facing cooling holes are provided adjacent to the stagnation line on the pressure side wall and oriented toward the leading edge.
Claims16
An airfoil for a gas turbine engine, comprising:
- pressure and suction side walls joined to one another at leading and trailing edges and forming an exterior airfoil surface extending in a radial direction to a tip, wherein a chord-wise direction extends from the leading edge to the trailing edge, a stagnation line located on the pressure side wall aft of the leading edge, a cooling passage provided between the pressure and suction side walls, and forward-facing cooling holes provided adjacent to the stagnation line on the pressure side wall and oriented toward the leading edge, a first centerline of the forward-facing cooling holes are at a first acute angle relative to a first line tangent to the exterior airfoil surface at the first centerline, the first acute angle and the first line are arranged in a first plane that extends in the chord-wise direction;
- a group of cooling holes clustered about the leading edge on both the pressure and suction side walls and distributed along a radial direction of the leading edge, the forward-facing cooling holes spaced aft of the group of cooling holes, wherein the forward-facing cooling holes are forward of the stagnation line and oriented toward the tip;
- aft-facing cooling holes provided aft of the stagnation line on the pressure side wall and oriented toward the trailing edge, a second centerline of the aft-facing cooling holes are at a second acute angle relative to a second line tangent to the exterior airfoil surface at the second centerline, the second acute angle and the second line are arranged in a second plane that extends in the chord-wise direction, the first and second acute angles are adjacent to the stagnation line;
- and
- wherein the airfoil has a Zweifel lift coefficient of greater than 1.1.
2 more elements
A gas turbine engine comprising:
- a compressor section;
- a combustor fluidly connected to the compressor section;
- a turbine section fluidly connected to the combustor, the turbine section includes:
- an array of turbine blades, each turbine blade includes an airfoil having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction to a tip, wherein a chord-wise direction extends from the leading edge to the trailing edge, a stagnation line provided on the pressure side wall aft of the leading edge, a cooling passage provided between the pressure and suction side walls, and forward-facing cooling holes provided adjacent to the stagnation line on the pressure side wall and oriented toward the leading edge, a first centerline of the forward-facing cooling holes are at a first acute angle relative to a first line tangent to the exterior airfoil surface at the first centerline, the first acute angle and the first line are arranged in a first plane that extends in the chord-wise direction;
- a group of cooling holes clustered about the leading edge on both the pressure and suction side walls and distributed along the radial direction, the forward-facing cooling holes spaced aft of the group of cooling holes, wherein the forward-facing cooling holes are forward of the stagnation line and oriented toward the tip;
- aft-facing cooling holes provided aft of the stagnation line on the pressure side wall and oriented toward the trailing edge, a second centerline of the aft-facing cooling holes are at a second acute angle relative to a second line tangent to the exterior airfoil surface at the second centerline, the second acute angle and the second line are arranged in a second plane that extends in the chord-wise direction, the first and second acute angles are adjacent to the stagnation line;
- and
- wherein the airfoil has a Zweifel lift coefficient of greater than 1.1.
5 more elements
Dependencies are inferred from the claim text.