Gas turbine engine airfoil
A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.
1. A compressor, comprising:
an airfoil configured to rotate about an axis, wherein the airfoil has a span measured radially from a root of the airfoil to a tip of the airfoil; and
a compressor case radially adjacent to the airfoil, wherein the airfoil and the compressor case define a clearance between the tip of the airfoil and a radially inner surface of the compressor case and wherein a ratio of the clearance to the span is between 1.5 and 2.5 percent, wherein a mass flow rate of the compressor is 3.0 pounds-mass per second or less, wherein the span of the airfoil is between about 14.73 millimeters and about 15.24 millimeters.
2. The compressor of claim 1 , wherein the ratio of the clearance to the span is between 2.0 and 2.5 percent.
3. The compressor of claim 1 , wherein the airfoil is a high pressure compressor airfoil.
4. The compressor of claim 1 , wherein the clearance is configured to prevent contact between the tip of the airfoil and the radially inner surface of the compressor case.
5. The compressor of claim 1 , wherein the airfoil is positioned in an aft end of the compressor.
6. A gas turbine engine, comprising:
an engine section comprising a compressor;
an airfoil positioned within the engine section and configured to rotate about an axis, wherein the airfoil has a span measured radially from a root of the airfoil to a tip of the airfoil; and
an engine case radially adjacent to the airfoil, wherein the airfoil and the engine case define a clearance between the tip of the airfoil and a radially inner surface of the engine case and wherein a ratio of the clearance to the span is between 1.5 and 2.5 percent, wherein a mass flow rate of the compressor is 3.0 pounds-mass per second or less, wherein the span of the airfoil is between about 14.73 millimeters and about 15.24 millimeters.
7. The gas turbine engine of claim 6 , wherein the ratio of the clearance to the span is between 2.0 and 2.5 percent.
8. The gas turbine engine of claim 6 , wherein the airfoil is a high pressure compressor airfoil.
9. The gas turbine engine of claim 8 , wherein the engine case is a compressor case.
10. The gas turbine engine of claim 6 , wherein the engine section is an aft portion of a high pressure compressor.
11. A method of increasing gas turbine engine efficiency, comprising:
forming an airfoil configured to rotate about an axis, wherein the airfoil has a span measured radially from a root of the airfoil to a tip of the airfoil, wherein the airfoil is a high pressure compressor airfoil having a mass flow rate of 3.0 pounds-mass per second or less;
disposing an engine case radially adjacent to the airfoil, wherein the airfoil and the engine case define a clearance between the tip of the airfoil and a radially inner surface of the engine case; and
forming a ratio of the clearance to the span in a range of 1.5 to 2.5 percent, wherein the forming the ratio of the clearance to the span includes increasing the span of the airfoil to between about 14.73 millimeters and about 15.24 millimeters.
12. The method of claim 11 , wherein the forming the ratio of the clearance to the span includes decreasing a diameter of the engine case relative to the span of the airfoil.
13. The method of claim 11 , wherein the engine case is a compressor case.