A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continu
A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
대표청구항▼
The invention claimed is: 1. A strut extending across a gaspath defined by an exhaust duct of a gas turbine engine, comprising an airfoil having at least a portion contained within the gaspath and defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and
The invention claimed is: 1. A strut extending across a gaspath defined by an exhaust duct of a gas turbine engine, comprising an airfoil having at least a portion contained within the gaspath and defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 7 set forth in one of Table 2 and Table 3, 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 strut in the exhaust duct, 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 strut as defined in claim 1, wherein the airfoil is made of sheet metal. 3. The strut as defined in claim 1, wherein the X and Y values are scalable as a function of the same constant or number while maintaining the same proportional relationship and airfoil shape. 4. The strut as defined in claim 1, wherein the X and Y coordinate values have a manufacturing tolerance of ±0.010 inch. 5. The strut as defined in claim 4, wherein the nominal profile defining the airfoil portion is for an uncoated airfoil. 6. The strut 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 o form an airfoil shape of the portion. 7. A strut extending across a gaspath of an exhaust duct of a gas turbine engine comprising an uncoated airfoil having at least one portion contained within the gaspath and defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 7 set forth in one of Table 2 and Table 3, 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 strut in the exhaust duct, the Z values are radial distances measured along the stacking line of the airfoil, the X and Y are coordinate values defining the profile at each distance Z, and wherein the X and Y values are scalable as a function of the same constant or number while maintaining the same proportional relationship and airfoil shape. 8. The strut as defined in claim 7, wherein the airfoil is made of sheet metal. 9. The strut as defined in claim 7, wherein the X and Y coordinate values have a manufacturing tolerance of ±0.010 inch. 10. The strut as defined in claim 7, 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. 11. An exhaust duct for a gas turbine engine comprising a gaspath and a plurality of thin struts extending across the gaspath, each thin strut including an airfoil having at least one portion contained within the gaspath and defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 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 struts, 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. The exhaust duct as defined in claim 11. wherein the exhaust duct defines a gaspath profile in accordance with Cartesian coordinate values of X and Z set forth in Table 1. 13. An exhaust strut comprising at least one airfoil having a surface lying substantially on the points of Table 2, the airfoil extending between inner and outer end portions defined generally by Table 1, and wherein the values of Table 2 are subject to relevant tolerance.
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