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US 9,752,439 B2Granted
Gas turbine engine airfoil
AssigneeUnited Technologies Corporation
InventorsEdward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Abstract
An airfoil arrangement of a turbine engine according to an example of the present disclosure includes adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope.
Claims21
An airfoil arrangement of a turbine engine comprising:
- adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope, wherein the gap/chord ratio is less than 0.8 from 80% span to 100% span, and the adjacent airfoils are rotatable blades.
A compressor section comprising:
- a plurality of rotatable compressor blades and a plurality of compressor vanes arranged about an axis;
- wherein adjacent rotatable compressor blades include pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the adjacent rotatable compressor blades have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope, wherein the gap/chord ratio is less than 1.04 from 80% span to 100% span.
A gas turbine engine comprising:
- a combustor section arranged between a compressor section and a turbine section;
- a fan section including an array of fan blades;
- and
- said compressor section including rotatable blades defining adjacent airfoils, the adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope, and the gap/chord ratio is less than 1.04 from 80% span to 100% span, and the adjacent airfoils are rotatable blades.
1 more element
Dependencies are inferred from the claim text.