Airfoil shape for compressor
A rotor blade is disclosed herein. The rotor blade comprises a nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1. Wherein X and Y are distances in millimeters which, when connected by smooth, continuing arcs, define airfoil profile sections at each distance Z in millimeters. The airfoil profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
1. A rotor blade comprising a nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1, wherein X and Y are distances in millimeters which, when connected by smooth, continuing arcs, define airfoil profile sections at each distance Z in millimeters, and wherein the airfoil profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.
2. The rotor blade of claim 1 , wherein the nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1 includes points within +/−1 mm in a direction normal to any surface of the complete airfoil shape.
3. The rotor blade of claim 1 , wherein a maximum thickness (Tmax) of the rotor blade starting from about 2.21% of a blade height up to about 60% of rotor blade height, is described by:
T max=−0.8646 *h+ 1.1087, where h is blade height percentage.
4. The rotor blade of claim 3 , wherein the maximum thickness of the rotor blade in a first subsequent region, ranging from about 60% to about 80% of the rotor blade height, is described by:
T max=−1.0209 *h+ 1.2058, where h is blade height percentage.
5. The rotor blade of claim 3 , wherein the maximum thickness of the rotor blade in a second subsequent region, ranging from 80% to 100% of the rotor blade height, is described by:
T max=−0.7618 *h+ 0.9985, where h is blade height percentage.
6. A rotor blade comprising:
a platform;
a root portion of the rotor blade connected to the platform; and
a blade surface ending in a tip portion, the blade surface comprising a cross-sectional airfoil shape,
wherein a thickness of the rotor blade varies as a function of rotor blade height in accordance with three different linear functions, and
wherein a maximum thickness (Tmax) of the rotor blade starting from about 2.21% of a blade height up to about 60% of rotor blade height, is described by a first one of the three linear functions as:
T max=−0.8646 *h+ 1.1087, where h is blade height percentage).
7. The rotor blade of claim 6 , wherein the rotor blade has a nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1, wherein X and Y are distances in millimeters which, when connected by smooth, continuing arcs, define airfoil profile sections at each distance Z in millimeters, and wherein the airfoil profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.
8. The rotor blade of claim 7 , wherein the nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1 includes points within +/−1 mm in a direction normal to any surface of the complete airfoil shape.
9. A rotor blade comprising:
a platform;
a root portion of the rotor blade connected to the platform; and
a blade surface ending in a tip portion, the blade surface comprising a cross-sectional airfoil shape,
wherein a thickness of the rotor blade varies as a function of rotor blade height in accordance with three different linear functions, and
wherein the maximum thickness of the rotor blade in a first subsequent region, ranging from about 60% to about 80% of the rotor blade height, is described by a second one of the three linear functions as:
T max=−1.0209 *h+ 1.2058, where h is blade height percentage.
10. The rotor blade of claim 9 , wherein the rotor blade has a nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1, wherein X and Y are distances in millimeters which, when connected by smooth, continuing arcs, define airfoil profile sections at each distance Z in millimeters, and wherein the airfoil profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.
11. The rotor blade of claim 10 , wherein the nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1 includes points within +/−1 mm in a direction normal to any surface of the complete airfoil shape.
12. A rotor blade comprising:
a platform;
a root portion of the rotor blade connected to the platform; and
a blade surface ending in a tip portion, the blade surface comprising a cross-sectional airfoil shape,
wherein a thickness of the rotor blade varies as a function of rotor blade height in accordance with three different linear functions, and
wherein the maximum thickness of the rotor blade in a second subsequent region, ranging from 80% to 100% of the rotor blade height, is described by a third one of the three linear functions as:
T max=−0.7618 *h+ 0.9985, where h is blade height percentage.
13. The rotor blade of claim 12 , wherein the rotor blade has a nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1, wherein X and Y are distances in millimeters which, when connected by smooth, continuing arcs, define airfoil profile sections at each distance Z in millimeters, and wherein the airfoil profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.
14. The rotor blade of claim 13 , wherein the nominal surface profile substantially in accordance with Cartesian coordinates X, Y and Z as set forth in TABLE 1 includes points within +/−1 mm in a direction normal to any surface of the complete airfoil shape.