Article of manufacture
An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
1. An article of manufacture comprising:
a rotor blade configured for use with a turbomachine, the rotor blade configured for attachment to a rotor wheel, the rotor blade having a neck width, a platform length, a platform angle, a platform height, a tang height, a tang depth and a dovetail circumferential width, wherein the rotor blade is configured to substantially reduce the possibility of attachment with an undesired third component by modification of at least one characteristic of the rotor blade, so that the modification of the at least one characteristic is matched by a complementary characteristic of the rotor wheel, the at least one characteristic comprising at least one of, the neck width, the platform length, the platform angle, the platform height, the tang height, the tang depth and the dovetail circumferential width; and
wherein the rotor blade has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape, the airfoil shape lies in an envelope within at least one of, +/−5% of a chord length in a direction normal to an airfoil surface location, or +/−0.25 inches in a direction normal to an airfoil surface location.
2. The article of manufacture of claim 1 , wherein the turbomachine is a compressor.
3. The article of manufacture of claim 2 , wherein the rotor blade and the rotor wheel comprise a first stage of the compressor.
4. The article of manufacture of claim 3 , wherein the third component is a rotor wheel comprising a second stage of the compressor, the first stage being different from the second stage.
5. The article of manufacture of claim 1 , the complementary characteristic of the second component comprising at least one of:
slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, and slot tang width.
6. The article of manufacture according to claim 1 , wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, decimal fraction, integer and mixed number.
7. The article of manufacture according to claim 1 , wherein a height of the article of manufacture is about 1 inch to about 20 inches.
8. An article of manufacture comprising:
a first component configured for use with a turbomachine, the first component configured for attachment to a second component, the first component having a neck width, a platform length, a platform angle, a platform height, a tang height, a tang depth and a dovetail circumferential width, wherein the first component is configured to substantially reduce the possibility of attachment with an undesired third component by modification of at least one characteristic of the first component, so that the modification of the at least one characteristic is matched by a complementary characteristic of the second component, the at least one characteristic comprising at least one of, the neck width, the platform length, the platform angle, the platform height, the tang height, the tang depth and the dovetail circumferential width;
wherein the first component has a suction-side nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape, the X, Y and Z coordinate values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up and scaled-down airfoil profile; and
the suction-side airfoil shape lies in an envelope within at least one of, +/−5% of a chord length in a direction normal to a suction-side airfoil surface location, or +/−0.25 inches in a direction normal to a suction-side airfoil surface location.
9. The article of manufacture of claim 8 , wherein the first component is a rotor blade and the second component is a rotor wheel.
10. The article of manufacture of claim 9 , wherein the turbomachine is a compressor.
11. The article of manufacture of claim 10 , wherein the rotor blade and the rotor wheel comprise a first stage of the compressor.
12. The article of manufacture of claim 11 , wherein the third component is a rotor wheel comprising a second stage of the compressor, the first stage being different from the second stage.
13. The article of manufacture of claim 9 , the at least one characteristic of the first component comprising at least one of:
neck width, platform length, platform angle, platform height, tang height, tang depth and dovetail circumferential width.
14. The article of manufacture of claim 9 , the complementary characteristic of the second component comprising at least one of:
slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, and slot tang width.
15. The article of manufacture according to claim 8 , wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, decimal fraction, integer and mixed number.
16. The article of manufacture according to claim 8 , wherein a height of the article of manufacture is about 1 inch to about 20 inches.
17. The article of manufacture according to claim 8 , further comprising the first component having a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y and Z set forth in the scalable table, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete pressure-side airfoil shape, the X, Y and Z values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up and scaled-down airfoil.