1. A wash cloth for exfoliating the skin comprising:
a plurality of vegetable fibers derived from the Malvaceae family of plants, and said plurality of vegetable fibers woven to define a primary fabric panel having a first side and an opposite second side.
2. The wash cloth as recited in claim 1 further comprising:
a pocket on said first side of said primary panel and said pocket being structured and disposed for holding a soap product.
3. The wash cloth as recited in claim 2 wherein said pocket comprises:
a secondary fabric panel of said woven plurality of vegetable fibers, and said secondary panel being attached to said primary panel to partially surround and enclose a pocket interior, and said secondary fabric panel being partially separated from said primary fabric panel to define a pocket opening for placement of the soap product within said pocket interior.
4. A wash cloth for exfoliating the skin comprising:
a plurality of vegetable fibers derived from the Malvaceae family of plants, and said plurality of vegetable fibers woven to define a primary fabric panel having a first side and an opposite second side, and a secondary fabric panel; and
said secondary fabric panel attached to said primary panel to define a pocket opening communicating with a pocket interior between said primary fabric panel and said secondary fabric panel for containing a soap product therein.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A turbine vane for a gas turbine engine comprising an airfoil having a portion defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 1 to 7 set forth in Table 2, wherein the point of origin of the orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine vane, the Z values are radial distances measured along the stacking line, the X and Y are coordinate values defining the profile at each distance Z.
2. The turbine vane as defined in claim 1 forming part of a high pressure turbine stage of the gas turbine engine.
3. The turbine vane as defined in claim 2, wherein the vane forms part of a second stage of a multi-stage high pressure turbine.
4. The turbine vane as defined in claim 1, wherein the turbine vane has a manufacturing tolerance of \xb10.030 inches in a direction perpendicular to the airfoil.
5. The turbine vane as defined in claim 1, wherein X and Y values define a set of points for each Z value which when connected by smooth continuing arcs define an airfoil profile section, the profile sections at the Z distances being joined smoothly with one another to form an airfoil shape of the portion.
6. A turbine vane for a gas turbine engine, the turbine vane having a cold coated intermediate airfoil portion defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 1 to 7 set forth in Table 2, wherein the point of origin of the orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine vane, the Z values are radial distances measured along the stacking line, the X and Y are coordinate values defining the profile at each distance Z.
7. The turbine vane as defined in claim 6 forming part of a vane of a high pressure turbine stage of the gas turbine engine.
8. The turbine vane as defined in claim 7, wherein the vane is part of a second stage of a two-stage high pressure turbine.
9. The turbine vane as defined in claim 6, wherein the turbine vane has a manufacturing tolerance of \xb10.030 inches.
10. The turbine vane as defined in claim 6, wherein X and Y values define a set of points for each Z value which when connected by smooth continuing arcs define an airfoil profile section, the profile sections at the Z distances being joined smoothly with one another to form an airfoil shape of the intermediate portion.
11. A turbine stator assembly for a gas turbine engine comprising a plurality of vanes, each vanes including an airfoil having an intermediate portion defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 1 to 7 set forth in Table 2, wherein the point of origin of the orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine vane, the Z values are radial distances measured along the stacking line, the X and Y are coordinate values defining the profile at each distance Z.
12. A high pressure turbine vane comprising at least one airfoil having a surface lying substantially on the points of Table 2, the airfoil extending between platforms defined generally by at least some of the coordinate values given in Table 1, wherein a fillet radius is applied around the airfoil between the airfoil and platforms.