Patent Grant
7329093
The present invention relates to a turbine and particularly relates to a nozzle blade airfoil profile for a gas turbine, particularly, the first stage nozzle blade profile.
The hot gas path of a turbine requires nozzle blade profiles that meet system requirements of efficiency and loading. The airfoil shape of the nozzle blades must optimize the interaction between other stages in the turbine, provide for aerodynamic efficiency and optimize aerodynamic life objectives. Particularly, nozzle blade airfoil profile affects nozzle stage positional stability and part life. Accordingly, there is a need for a nozzle airfoil profile which optimizes these objectives.
In a preferred embodiment of the present invention, there is provided a nozzle blade for a turbine having an airfoil, the airfoil having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I which define a plurality of radially spaced profile sections forming the nominal profile, the Z coordinate values for each profile section being radial distances from the turbine axis to a portion of a surface of revolution about the turbine axis containing the profile section, and the X and Y values for each profile section being coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion, the radially spaced profile sections being joined smoothly with one another to form the nominal airfoil profile.
In a further preferred embodiment of the present invention, there is provided a nozzle blade for a turbine having an airfoil, the airfoil having a shape in an envelope within ±0.160 inches in a direction normal to any airfoil surface location, the airfoil having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I which define a plurality of radially spaced profile sections forming the nominal profile, the Z coordinate values for each profile section being radial distances from the turbine axis to a portion of a surface of revolution about the turbine axis containing the profile section, and the X and Y values for each profile section being coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion, the radially spaced profile sections being joined smoothly with one another to form the nominal airfoil profile.
In an even further preferred embodiment of the present invention, there is provided a turbine having a plurality of nozzle blades forming a portion of a turbine stage, each nozzle blade being in the shape of an airfoil, each airfoil having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I which define a plurality of radially spaced profile sections forming the nominal profile, the Z coordinate values for each profile section being radial distances from the turbine axis to a portion of a surface of revolution about the turbine axis containing the profile section, and the X and Y values for each profile section being coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion, the radially spaced profile sections being joined smoothly with one another to form the nominal airfoil profile.
In still another aspect of the present invention, a turbine having a plurality of nozzle blades forming a portion of a turbine stage, each nozzle blade being in the shape of an airfoil, each the airfoil having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I which define a plurality of radially spaced profile sections forming the nominal profile, the Z coordinate values for each profile section being radial distances from the turbine axis to a portion of a surface of revolution about the turbine axis containing the profile section, and the X and Y values for each profile section being coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion, the radially spaced profile sections being joined smoothly with one another to form the nominal airfoil profile, each airfoil having a shape within ±0.0160 inches in a direction normal to any airfoil surface location.
Referring now to
Referring to
Each of the first stage nozzle blades has an airfoil profile defined by a Cartesian coordinate system of X, Y and Z values. The coordinate values are set forth in inches in Table I below. The Cartesian coordinate system includes orthogonally related X, Y and Z axes. The X axis lies along the turbine rotor center line, i.e., the rotor axis. The Z axis extends along radii from the center line of the turbine rotor to the X and Y coordinate values for the respective sets of X, Y and Z coordinate values. That is, each Z distance commences at zero along the turbine axis and extends to a point defined by the X and Y coordinate values for those X, Y and Z coordinate values.
The airfoil profile sections between the inner and outer side walls are given in eleven sets of X, Y and Z coordinate values, and hence eleven profile sections, represented by the dashed lines in
By defining X and Y coordinate values at selected locations in the Z direction along radii from the turbine axis, the profile of each airfoil section of the eleven sections can be ascertained. By connecting the X, Y and Z values in each profile section with smooth continuing arcs, the profile of the blade at each section is ascertained. The surface profiles at the various surface locations between the profile sections are connected smoothly to one another to form a nominal airfoil profile.
The tabular values given in Table I are in inches and represent the airfoil profiles at ambient, non-operating or non-hot conditions and are for an uncoated airfoil. The X, Y and Z coordinate values given in Table I are in scientific notation represented by the letter E followed by numerical values. The numerical values represent the number of spaces to move the decimal point of the number preceding the scientific notation E to give the actual value in inches. The plus or minus signs indicate the direction of movement of the decimal points, i.e., the plus sign signals movement of the decimal point to the right and the minus sign signals movement of the decimal point to the left. The 78 points defined by the X, Y and Z coordinate values of Table I for each profile section are for a nominal cold or room temperature profile for each profile section of the airfoil.
There are typical manufacturing tolerances as well as coatings which must be accounted for in the actual profile of the airfoil. Accordingly, the values for the profile given in Table I are for a nominal airfoil. It will therefore be appreciated that typical manufacturing tolerances, i.e., ±values and coating thicknesses are added to or subtracted from the X, Y and Z values given in Table I below. Accordingly, a distance of ±0.160 inches in a direction normal to any surface location along the airfoil profile, defines an airfoil envelope for this particular airfoil design. In a preferred embodiment, the blade airfoil profiles given in Table I below are for the first stage blades of the turbine.
The coordinate values given in Table I below are in inches and provides the preferred nominal profile envelope.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
| Number | Name | Date | Kind |
|---|---|---|---|
| 5980209 | Barry et al. | Nov 1999 | A |
| 6398489 | Burdgick et al. | Jun 2002 | B1 |
| 6450770 | Wang et al. | Sep 2002 | B1 |
| 6461109 | Wedlake et al. | Oct 2002 | B1 |
| 6461110 | By et al. | Oct 2002 | B1 |
| 6474948 | Pirolla et al. | Nov 2002 | B1 |
| 6503054 | Bielek et al. | Jan 2003 | B1 |
| 6503059 | Frost et al. | Jan 2003 | B1 |
| 6558122 | Xu et al. | May 2003 | B1 |
| 6685434 | Humanchuk et al. | Feb 2004 | B1 |
| 6715990 | Arness et al. | Apr 2004 | B1 |
| 6722852 | Wedlake et al. | Apr 2004 | B1 |
| 6722853 | Humanchuk et al. | Apr 2004 | B1 |
| 6736599 | Jacks et al. | May 2004 | B1 |
| 6739838 | Bielek et al. | May 2004 | B1 |
| 6739839 | Brown et al. | May 2004 | B1 |
| 6769878 | Parker et al. | Aug 2004 | B1 |
| 6769879 | Cleveland et al. | Aug 2004 | B1 |
| 6779977 | Lagrange et al. | Aug 2004 | B2 |
| 6779980 | Brittingham et al. | Aug 2004 | B1 |
| 6808368 | Tomberg et al. | Oct 2004 | B1 |
| 6832897 | Urban | Dec 2004 | B2 |
| 6854961 | Zhang et al. | Feb 2005 | B2 |
| 6857855 | Snook et al. | Feb 2005 | B1 |
| 6866477 | Arness et al. | Mar 2005 | B2 |
| 6881038 | Beddard et al. | Apr 2005 | B1 |
| 6884038 | Hyde et al. | Apr 2005 | B2 |
| 6887041 | Coke et al. | May 2005 | B2 |
| 6910868 | Hyde et al. | Jun 2005 | B2 |
| 6932577 | Strohl et al. | Aug 2005 | B2 |
| 7001147 | Phillips et al. | Feb 2006 | B1 |
| 7094034 | Fukuda et al. | Aug 2006 | B2 |
| 7186090 | Tomberg et al. | Mar 2007 | B2 |
| 20030017052 | Frost et al. | Jan 2003 | A1 |
| 20030021680 | Bielek et al. | Jan 2003 | A1 |
| 20040057833 | Arness et al. | Mar 2004 | A1 |
| 20040115058 | Lagrange et al. | Jun 2004 | A1 |
| 20040175271 | Coke et al. | Sep 2004 | A1 |
| 20040223849 | Urban | Nov 2004 | A1 |
| 20040241002 | Zhang et al. | Dec 2004 | A1 |
| 20050013692 | Snook et al. | Jan 2005 | A1 |
| 20050013695 | Hyde et al. | Jan 2005 | A1 |
| 20050019160 | Hyde et al. | Jan 2005 | A1 |
| 20050025618 | Arness et al. | Feb 2005 | A1 |
| 20050031453 | Snook et al. | Feb 2005 | A1 |
| 20050079061 | Beddard et al. | Apr 2005 | A1 |
| 20060024159 | Phillips et al. | Feb 2006 | A1 |
| 20060073014 | Tomberg et al. | Apr 2006 | A1 |
| 20060216144 | Sullivan et al. | Sep 2006 | A1 |
| 20070048143 | Noshi | Mar 2007 | A1 |
| 20070154316 | Clarke | Jul 2007 | A1 |
| 20070154318 | Saltman et al. | Jul 2007 | A1 |
| 20070177980 | Keener et al. | Aug 2007 | A1 |
| 20070177981 | Vandeputte et al. | Aug 2007 | A1 |
| 20070183895 | Sheffield | Aug 2007 | A1 |
| 20070183896 | Jay et al. | Aug 2007 | A1 |
| 20070183897 | Sadler et al. | Aug 2007 | A1 |
| 20070183898 | Hurst et al. | Aug 2007 | A1 |
| 20070201983 | Arinci et al. | Aug 2007 | A1 |
| 20070207035 | Girgis et al. | Sep 2007 | A1 |
| 20070207036 | Girgis et al. | Sep 2007 | A1 |
| 20070207037 | Girgis et al. | Sep 2007 | A1 |
| 20070207038 | Girgis et al. | Sep 2007 | A1 |
| Number | Date | Country | |
|---|---|---|---|
| 20070177981 A1 | Aug 2007 | US |
