HIGH LIFT TRANSONIC TURBINE BLADE

• US 20090162204A1
• Filed: 08/16/2006
• Published: 06/25/2009
• Est. Priority Date: 08/16/2006
• Status: Active Grant

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Aggarwala, Andrew S., Gacek, Richard E., Staubach, Joseph B.
• Granted Patent: US 7,581,930 B2
• Time in Patent Office: Days
• US Class Current: 416/204.R
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates

Abstract

A turbine blade system including a blade airfoil having an airfoil shape with the blade airfoil having a nominal profile substantially in accordance with normalized Cartesian coordinate values Z set forth in a table 1 below and which values are dimensionless values that are convertible to corresponding absolute distance values that define nominal airfoil profile sections and which, when joined smoothly with adjacent ones thereof, form a complete nominal airfoil shape that is substantially matched by the airfoil shape of the blade airfoil. This blade airfoil can be supported on a ring platform having a support surface with a support surface shape in the vicinity of the location at which that blade airfoil is supported thereon formed in a similar manner.

Claims

1. A turbine blade system including a blade airfoil having an airfoil shape, the blade airfoil having a nominal profile substantially in accordance with normalized Cartesian coordinate values of X, Y and Z set forth in Table 1 herein and which values are dimensionless values that are convertible to corresponding absolute distance values through manipulating them in accord with corresponding normalization equations, and wherein X and Y absolute distance values, when connected by smooth continuing arcs, define nominal airfoil profile sections at each Z absolute distance value, and the nominal airfoil profile sections, when joined smoothly with adjacent ones thereof in accord with Tables 2 and 3 herein, form a complete nominal airfoil shape that is substantially matched by the airfoil shape of the blade airfoil.

2. The turbine blade system of claim 1 further comprising a platform ring on which the blade airfoil is supported along with a plurality of similar blade airfoils positioned about the circumference of the ring platform.

3. The turbine blade system of claim 1 wherein the normalization equations allow the X, Y and Z absolute distance values to be scaled as a function of selected parameters to thereby provide a nominal airfoil shape that is scaleable over ranges of absolute distance values for providing a selection of alternative sizes for corresponding blade airfoils.

4. The turbine blade system of claim 1 wherein the blade airfoil has an airfoil shape that occurs anywhere in a spatial region about a nominal airfoil shape that is bounded by being within ±

0.050 inches in directions normal to any locations on the nominal airfoil shape.

5. The turbine blade system of claim 1 wherein the height of the blade airfoil from root to tip is 1.905000 inches.

6. The turbine blade system of claim 1 wherein the normalization equations depend on the normalization parameters blade root axial chord represented as Bx_root, the blade span (form the ID section to the OD section) represented as h, the blade root pitch represented as Pitch_root, and the blade root radius represented as R_root.

7. The turbine blade system of claim 2 wherein the ring platform has a support surface with a support surface shape in the vicinity of the location at which the blade airfoil is supported thereon with that support surface smoothly joining with the airfoil shape, the support surface having a nominal profile substantially in accordance with normalized Cartesian coordinate values of X, Y and Z set forth in Table 4 herein and which values are dimensionless values that are convertible to corresponding absolute distance values through manipulating them in accord with corresponding normalization equations, and wherein X and Y absolute distance values at various Z absolute distance values, when connected by smooth continuing arcs, form a nominal support surface shape substantially matched by the support surface shape of the support surface.

8. The turbine blade system of claim 2 wherein a corresponding radius of the ring platform extends through each of the blade airfoils and each of the blade airfoils is positioned selectively rotated within ±

10°

with respect the radius corresponding thereto from the position set forth therefore in Tables 1 and 4 as converted to absolute distance values.

9. The turbine blade system of claim 7 wherein the support surface has a support surface shape that occurs anywhere in a spatial region about a nominal support surface shape that is bounded by being within ±

0.050 inches in directions normal to any locations on the nominal support surface shape.

10. A ring platform for a turbine blade system on which a plurality of blade airfoils are supported positioned about the circumference of the ring platform, the ring platform having a support surface with a support surface shape in the vicinity of the location at which a blade airfoil is supported thereon with that support surface smoothly joining with the airfoil shape of that blade airfoil, the support surface having a nominal profile substantially in accordance with normalized Cartesian coordinate values of X, Y and Z set forth in Table 4 and which values are dimensionless values that are convertible to corresponding absolute distance values through manipulating them in accord with corresponding normalization equations, and wherein X and Y absolute distance values at various Z absolute distance values, when connected by smooth continuing arcs, form a nominal support surface shape substantially matched by the support surface shape of the support surface.

11. The turbine blade system of claim 10 wherein the support surface has a support surface shape that occurs anywhere in a spatial region about a nominal support surface shape that is bounded by being within ±

0.050 inches in directions normal to any locations on the nominal support surface shape.