Compressor stator vane airfoil

Abstract

A stator vane is provided. The stator vane includes an airfoil having a nominal suction side profile substantially according to suction side Cartesian coordinate values X, Y, and Z listed in Table I. Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at the base of the airfoil. The Cartesian coordinate values of X, Y and Z are dimensionless values that can be converted into dimensional distances expressed in distance units by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil expressed in distance units. The X and Y values are connected by smoothly continuous arcs to define a suction side profile cross-section at each Z value. The suction side profile cross-sections at the Z-value smoothly engage one another to form a complete airfoil suction side shape.

Description

Technical Field

[0001] The present disclosure relates to an airfoil for a compressor stator vane disposed within a stage of a compressor section of a land-based gas turbine system, and more particularly, to a shape defining a profile of the airfoil of the compressor stator vane. Background Art

[0002] Some simple cycle or combined cycle power plant systems employ turbines in their design and operation. Generally, the turbines employ airfoils (e.g., stator vanes or nozzles and rotor blades) that are exposed to a fluid flow during operation. These airfoils are configured to aerodynamically interact with the fluid flow and transfer energy to or from the fluid flow as part of power generation. For example, the airfoils can be used to compress a fluid, generate thrust, convert kinetic energy to mechanical energy, and / or convert thermal energy to mechanical energy. Due to these interactions and conversions, the aerodynamic characteristics of these airfoils can result in losses that have an impact on system and turbine operation, performance, thrust, efficiency, and power. Summary of the Invention

[0003] Aspects and advantages of the stator vane and turbine in accordance with the present disclosure will be set forth in part in the following description, or will be obvious from the description, or may be learned by practice of the technique.

[0004] According to one embodiment, a stator vane is provided. The stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially according to the Cartesian coordinate values of X, Y, and Z listed in Table I. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at the base of the airfoil. The Cartesian coordinate values of X, Y, and Z are dimensionless values that can be converted to a dimensional distance in distance units by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in distance units. The X values and Y values are connected by smooth continuous arcs to define an airfoil profile section at each Z value. The airfoil profile sections at the Z values are smoothly joined to each other to form a complete airfoil shape.

[0005] According to another embodiment, a stator vane is provided. The stator vane includes an airfoil having a nominal suction side profile substantially according to the suction side Cartesian coordinate values X, Y, and Z listed in Table I. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at the base of the airfoil. The Cartesian coordinate values of X, Y, and Z are dimensionless values that can be converted to a dimensional distance in distance units by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in distance units. The X values and Y values are connected by smooth continuous arcs to define a suction side profile cross-section at each Z value. The suction side profile cross-sections at the Z values are smoothly joined to each other to form a complete airfoil suction side shape.

[0006] According to yet another embodiment, a turbine is provided. The turbine includes a compressor section, a turbine section positioned downstream of the compressor section, and a combustion section positioned downstream of the compressor section and upstream of the turbine section. The turbine further includes a stator vane disposed within one of the compressor section or the turbine section. The stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially according to the Cartesian coordinate values of X, Y, and Z listed in Table I. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at the base of the airfoil. The Cartesian coordinate values of X, Y, and Z are dimensionless values that can be converted to a dimensional distance in distance units by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in distance units. The X values and Y values are connected by smooth continuous arcs to define an airfoil profile cross-section at each Z value. The airfoil profile cross-sections at the Z values are smoothly joined to each other to form a complete airfoil shape.

[0007] These and other features, aspects, and advantages of the stator vane and turbine of the present invention will become better understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the technology of the present invention and, together with the description, serve to explain the principles of the technology of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] The complete and enabling disclosure of the stator vane and turbine of the present invention, including the best mode of making and using the systems and methods of the present invention, to one of ordinary skill in the art, is set forth in this specification with reference to the accompanying drawings, in which:

[0009] Figure 1 is a schematic view of a turbine according to an embodiment of the present disclosure;

[0010] Figure 2 shows a cross-sectional side view of a compressor section of a turbine according to an embodiment of the present disclosure (e.g., Figure 1 of the turbine);

[0011] Figure 3 shows a perspective view of a stator vane that can be used in a compressor section of Figure 2 ; and

[0012] Figure 4 shows an airfoil profile cross-section of an airfoil taken along line 4-4 shown in Figure 3 ; and

[0013] Figure 5 shows a graph of the stagger angle distribution of airfoils belonging to stator vanes provided in a specific stage of a compressor section, according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0014] Reference will now be made in detail to embodiments of the stator vanes and turbines of the present invention, one or more examples of which are shown in the drawings. Each example is provided by way of explaining the technology of the present invention, and not as a limitation of the technology of the present invention. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the technology of the present invention without departing from the scope or spirit of the technology of the present invention as protected by the claims. For example, features illustrated or described as part of one embodiment can be used in another embodiment to yield yet another embodiment. Accordingly, the present disclosure is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0015] The detailed description uses numerical and alphabetical names to refer to features in the drawings. Similar or like names in the drawings and the description have been used to refer to similar or like components of the present invention. As used herein, the terms "first", "second", and "third" may be used interchangeably to distinguish one component from another, and are not intended to denote the position or importance of the individual components.

[0016] As used herein, the terms "upstream" (or "upward") and "downstream" (or "downward") refer to the relative direction with respect to the flow of fluid in a fluid passage. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction towards which the fluid flows. The term "radially" refers to a relative direction that is substantially perpendicular to the axial centerline of a particular component, the term "axially" refers to a relative direction that is substantially parallel and / or coaxially aligned with the axial centerline of a particular component, and the term "circumferentially" refers to a relative direction that extends around the axial centerline of a particular component.

[0017] Approximate terms, such as "substantially", "essentially", or "about", include values within ten percent greater than or less than a specified value. When used in the context of an angle or a direction, such terms include within ten degrees greater than or less than the stated angle or direction. For example, "substantially vertical" includes a direction within ten degrees of vertical in any direction (e.g., clockwise or counterclockwise).

[0018] Referring now to the drawings, Figure 1 There is shown a schematic illustration of one embodiment of a turbine, which in the illustrated embodiment is a gas turbine 10. Although an industrial or land-based gas turbine is shown and described herein, the present disclosure is not limited to industrial and / or land-based gas turbines unless otherwise specified in the claims. For example, the stator vane airfoils as described herein can be used in any type of turbine, including but not limited to steam turbines, aircraft gas turbines, or marine gas turbines.

[0019] As shown, the gas turbine 10 generally includes an inlet section 12, a compressor section 14 disposed downstream of the inlet section 12, one or more burners (not shown) within a burner section 16 disposed downstream of the compressor section 14, a turbine section 18 disposed downstream of the burner section 16, and an exhaust section 20 disposed downstream of the turbine section 18. Additionally, the gas turbine 10 can include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18.

[0020] The multi-stage axial-flow compressor section or compressor section 14 generally can include a plurality of rotor disks 24 (one shown) and a plurality of rotor blades 44 that extend radially outward from each rotor disk 24 and are connected to each rotor disk. Each rotor disk 24 in turn can be coupled to or form a part of a shaft 22 that extends through the compressor section 14. The compressor section 14 can also include one or more stator vanes 50 circumferentially disposed about the shaft 22. The stator vanes 50 can be fixed to a stationary housing or compressor housing 48 that extends circumferentially around the rotor blades 44.

[0021] The turbine section 18 generally can include a plurality of rotor disks 28 (one shown) and a plurality of rotor blades 30 that extend radially outward from each rotor disk 28 and are interconnected to each rotor disk. Each rotor disk 28 in turn can be coupled to or form a part of a shaft 22 that extends through the turbine section 18. The turbine section 18 also includes a turbine housing 33 that circumferentially surrounds the turbine portion of the shaft 22 and the rotor blades 30, thereby at least partially defining a hot gas path 32 through the turbine section 18. The turbine housing 33 can be configured to support a plurality of stages of fixed nozzles 29 that extend radially inward from the inner circumference of the turbine housing 33.

[0022] During operation, a working fluid such as air flows through the inlet section 12 and into the compressor section 14, where the air is gradually compressed, thereby supplying pressurized air to the burners in the burner section 16. The pressurized air is mixed with fuel and burned in the burners to produce combustion gases 34. The combustion gases 34 flow from the burner section 16 through the hot gas path 32 into the turbine section 18, where energy (kinetic energy and / or thermal energy) is transferred from the combustion gases 34 to the rotor blades 30, causing the shaft 22 to rotate. Then, the mechanical rotational energy can be used to power the compressor section 14 and / or generate electricity. Then, the exhaust combustion gases 34 (sometimes referred to as "flue gas" or "exhaust gas") leaving the turbine section 18 can be discharged from the gas turbine 10 via the exhaust section 20.

[0023] Figure 2 A cross-sectional side view of an embodiment of the compressor section 14 of a Figure 1 gas turbine 10 according to an embodiment of the present disclosure is shown, and the compressor section is shown as a multi-stage axial-flow compressor section 14. As Figure 1 and Figure 2 shown, the gas turbine 10 can define a cylindrical coordinate system. The cylindrical coordinate system can define an axial direction A (e.g., a downstream direction) parallel to and / or along the axial centerline 23 of the gas turbine 10, a radial direction R perpendicular to the axial centerline 23, and a circumferential direction C extending around the axial centerline 23.

[0024] In operation, air 15 can enter the compressor section 14 through the inlet section 12 along the axial direction A and can be pressurized in the multi-stage axial-flow compressor section 14. The compressed air can then be mixed with fuel to burn in the burner section 16 to drive the turbine section 18, which causes the shaft 22 to rotate in the circumferential direction C and thus causes the multi-stage axial-flow compressor section 14 to rotate. The rotation of the shaft 22 also causes one or more rotor blades 44 (e.g., compressor rotor blades) within the multi-stage axial-flow compressor section 14 to suck in and pressurize the air received by the inlet section 12.

[0025] The multi-stage axial-flow compressor section 14 can include a rotor assembly 46 having a plurality of rotor disks 24. The rotor blades 44 can extend radially outward from the rotor disks 24. The entire rotor assembly 46 (e.g., the rotor disks 24 and the rotor blades 44) can rotate in the circumferential direction C during the operation of the gas turbine 10. The rotor assembly 46 can be surrounded by a compressor housing 48. The compressor housing can be static or stationary such that the rotor assembly 46 rotates relative to the compressor housing 48. Stator vanes 50 (e.g., variable stator vanes and / or fixed stator vanes) can extend radially inward from the compressor housing 48.

[0026] As Figure 2As shown, one or more stages of the stator vanes 50 can be variable stator vanes 51 such that the angle of the stator vanes 50 can be selectively actuated (e.g., by the controller 200). For example, in Figure 2 the illustrated embodiment, the first two stages (e.g., S1 and S2) of the compressor section 14 can include variable stator vanes 51. In many embodiments, as shown, the rotor blades 44 and the stator vanes 50 can be arranged in an alternating manner in a plurality of stages such that most of the stages of the rotor blades 44 are disposed between two stages of the stator vanes 50 in the axial direction A.

[0027] In some embodiments, the compressor housing 48 or the inlet section 12 of the compressor section 14 can have one or more sets of inlet guide vanes 52 (IGV) (e.g., variable IGV stator vanes). The inlet guide vanes 52 can be mounted to the compressor housing 48, can be spaced apart from each other in the circumferential direction C, and are operable to control the amount of air 15 entering the compressor section 14. Additionally, the outlet 56 of the compressor section 14 can have a set of outlet guide vanes (not shown).

[0028] In an exemplary embodiment, as Figure 2 shown, the variable stator vanes 51 and the IGV 52 can each be configured to change their vane angles relative to the air flow (e.g., air stream) by rotating the vanes 51, 52 about a rotational axis (e.g., a radially oriented vane shaft). However, each variable stator vane 51 and each IGV 52 can be stationary relative to the rotor blades 44 in other ways. In certain embodiments, the variable stator vanes 51 and the IGV 52 can be coupled to an actuator 19 (e.g., electrically driven, pneumatically driven, or hydraulically driven). The actuator 19 can be operably communicated with the controller 200 (e.g., electrically). The controller is operable to selectively change the vane angles. In other embodiments, all of the stator vanes 50 can be fixed such that the stator vanes 50 are configured to remain in a fixed angular position (e.g., the vane angle does not change).

[0029] The compressor section 14 may include a plurality of rows or stages arranged in a serial flow order, such as 2 to 30, 2 to 25, 2 to 20, 2 to 14, or 2 to 12 rows or stages, or any specific number or range therebetween. Each stage may include a plurality of rotor blades 44 (attached to the rotor disk 24 and circumferentially spaced about the axial centerline 23) and a plurality of stator vanes 50 (attached to the compressor housing 48 and circumferentially spaced about the axial centerline 23). In each stage, the multistage axial-flow compressor section 14 may include 2 to 1000, 5 to 500, or 10 to 100 circumferentially arranged rotor blades 44, and 2 to 1000, 5 to 500, or 10 to 100 circumferentially arranged stator vanes 50. Specifically, an exemplary embodiment of the multistage axial-flow compressor section 14 includes 12 stages (e.g., S1 - S12).

[0030] It should be understood that each stage has a set of rotor blades 44 disposed at a first axial position and a set of stator vanes 50 disposed at a second axial position along the length of the compressor section 14. In other words, each stage has rotor blades 44 and stator vanes 50 that are axially offset from each other such that the compressor section 14 has an alternating arrangement of rotor blades 44 and stator vanes 50 that are sequentially disposed along the length of the compressor section 14. Each set of rotor blades 44 extends circumferentially in the circumferential direction C about the shaft 22 (e.g., in a spaced-apart arrangement), and each set of stator vanes 50 extends circumferentially in the circumferential direction C within the compressor housing 48 (e.g., in a spaced-apart arrangement).

[0031] Although the compressor section 14 may include more or fewer stages than shown, Figure 2 an embodiment of the compressor section 14 is shown having twelve stages arranged in a serial flow order and identified as follows: a first stage S1, a second stage S2, a third stage S3, a fourth stage S4, a fifth stage S5, a sixth stage S6, a seventh stage S7, an eighth stage S8, a ninth stage S9, a tenth stage S10, an eleventh stage S11, and a twelfth stage S12. The IGV 52 is located upstream (i.e., forward) of the first stage S1. The OGV, if used, is located downstream (i.e., backward) of the twelfth stage S12.

[0032] In some embodiments, each stage may include rotor blades 44 and stator vanes 50 (e.g., fixed stator vanes 50 and / or variable stator vanes 51, 52). As used herein, rotor blades 44 disposed within one of the sections S1 - S12 of the compressor section 14 may be referred to by any stage in which they are disposed, e.g., "first stage compressor rotor blades", "second stage compressor rotor blades", "third stage compressor rotor blades", etc. Similarly, stator vanes 50 disposed within one of the sections S1 - S12 of the compressor section 14 may be referred to by any stage in which they are disposed, e.g., "third stage compressor stator vanes", "fourth stage compressor stator vanes", "fifth stage compressor stator vanes", etc.

[0033] In use, the rotor blades 44 may rotate circumferentially within the compressor housing 48 about the axial centerline 23 between and relative to the stator vanes 50. Rotation of the rotor blades 44 may cause air to enter the inlet section 12. The air is then compressed as it passes through the various stages (e.g., first stage S1 to twelfth stage S12) of the compressor section 14 and moves axially downstream of the multi - stage axial compressor section 14. The compressed air may then exit through the outlet 56 of the multi - stage axial compressor section 14. The compressed air leaving the compressor section 14 may be directed to the burner section 16 and mixed with fuel for combustion. Air from one or more stages of the compressor section 14 may also be directed to the turbine section 18 or elsewhere in the gas turbine 10 for cooling and / or sealing.

[0034] The stages of the IGV 52 and rotor blades 44 (e.g., S1 - S12) and the stator vanes 50 of the compressor section 14 may be grouped for reference purposes into one or more sections or parts of the compressor section 14. For the purpose of grouping, parts of the compressor section 14 may be expressed as a percentage, such as a percentage of the compressor section 14 from the inlet (e.g., 0% of the compressor section 14) to the outlet (e.g., 100% of the compressor section 14) in the axial or downstream direction. In this way, the compressor section 14 may include a primary stage 60, an intermediate stage 62, and a rear stage 64 in serial flow order. Specifically, the primary stage 60 may include from about 0% to about 25% of the compressor section 14 (e.g., from the IGV 52 to about the third stage S3). The intermediate stage 62 may include from about 25% to about 75% of the compressor section 14 (e.g., from about the fourth stage S4 to about the ninth stage S9). The rear stage 64 may include from about 75% to about 100% of the compressor section 14 (e.g., from about the tenth stage S10 to the twelfth stage S12 and / or the OGV, not shown).

[0035] Accordingly, the Cartesian coordinate data contained in Table I may correspond to the airfoil shape of the airfoil 100 disposed within the intermediate stage 62 of the compressor section 14. For example, in an exemplary embodiment, the Cartesian coordinate data contained in Table I may correspond to the airfoil shape of the airfoil 100 on the stator vane 50 disposed within the seventh stage S7 of the compressor section 14.

[0036] However, in various other embodiments, Table I may contain Cartesian coordinate data of the airfoil shape of the airfoil 100, and the airfoil may be disposed on the stator vane 50 or the rotor blade 44 in any stage S1 - S12 of the compressor section 14. Accordingly, unless specifically recited in the claims, the airfoil shape defined by Table I should not be limited to any particular stage of the compressor section 14.

[0037] Figure 3 A perspective view of a stator vane 50 according to an embodiment of the present disclosure is shown, which may be incorporated into any stage (e.g., S1 to S12) of the compressor section 14.

[0038] As shown, the stator vane 50 includes an airfoil 100 that defines an airfoil shape 150. The airfoil 100 includes a pressure side surface or profile 102 and an opposing suction side surface or profile 104. The pressure side surface 102 and the suction side surface 104 meet or converge at the leading edge 106 and the trailing edge 108 of the airfoil 100. A chord line 110 extends between the leading edge 106 and the trailing edge 108 such that the pressure side surface 102 and the suction side surface 104 can be said to extend along the chord or chordwise between the leading edge 106 and the trailing edge 108. The leading edge 106 and the trailing edge 108 may be described as the dividing line or intersection line between the suction side surface 104 and the pressure side surface 102, respectively. In other words, the suction side surface 104 and the pressure side surface 102 are joined together along the leading edge 106 and the trailing edge 108, thereby defining a cross-section of the airfoil shape that gradually varies in the length direction (or "span") along the airfoil 100.

[0039] In operation, the stator vanes 50 can be stationary components that do not move circumferentially along the circumferential direction C. For example, the stator vanes 50 can be coupled to the compressor housing 48 and extend radially inwardly from the compressor housing. Each set (or stage) of stator vanes 50 within the compressor section 14 can be axially disposed between two sets (or stages) of rotor blades 44 that rotate along the circumferential direction C. For example, the rotor blades 44 rotate about the turbine axial centerline 23, thereby applying torque to the working fluid (such as air 15), and thus increasing the energy level of the fluid as the working fluid traverses the respective stages S1 to S12 of the multi-stage axial flow compressor section 14 on its way to the burner section 16. The stator vanes 50 can be adjacent to (e.g., upstream and / or downstream) one or more sets of rotor blades 44. The stator vanes 50 slow down the working fluid during the rotation of the rotor blades 44, thereby converting the moving circumferential component of the working fluid flow into pressure. Thus, the continuous rotation of the rotor blades 44 produces a continuous flow of compressed working fluid that is suitable for combustion via the burner section 16.

[0040] As Figure 3 shown, the airfoil 100 includes a root or first end 112 that intersects and extends radially inwardly from the base or platform 114 of the stator vane 50. The airfoil 100 radially terminates at a second end or radial tip 116 of the airfoil 100. In some embodiments (not shown), the stator vane 50 can include a tip shroud or tip platform that extends generally parallel to the base 114 from the radial tip 116. The pressure side surface 102 and the suction side surface 104 can be said to extend along the span or spanwise direction 118 between the root 112 and / or the platform 114 and the radial tip 116 of the airfoil 100. In other words, each stator vane 50 includes an airfoil 100 having opposing pressure side surface 102 and suction side surface 104 that extend along the chord or chordwise 110 between opposing leading edge 106 and trailing edge 108, and extend along the span or spanwise direction 118 between the root 112 and the radial tip 116 of the airfoil 100.

[0041] In a particular configuration, the airfoil 100 can include a corner 72 formed between the platform 114 and the airfoil 100 near the root 112. The corner 72 can include a welded or brazed corner that can be formed via conventional MIG welding, TIG welding, brazing, etc., and can include a profile that can reduce hydrodynamic losses due to the presence of the corner 72. In a particular embodiment, the platform 114, the airfoil 100, and the corner 72 can be formed as a single component, such as by casting and / or machining and / or additive manufacturing (such as 3D printing) and / or any other suitable technique now known or later discovered and / or developed.

[0042] In various embodiments, the stator vane 50 may include a mounting portion 74 (such as a dovetail joint) configured to connect and / or secure the stator vane 50 to the compressor housing 48. For example, the mounting portion 74 may include a T-shaped structure, a hook, one or more lateral protrusions, one or more lateral slots, or any combination thereof. The mounting portion 74 (e.g., the dovetail joint) may be configured to be mounted into the compressor housing 48 in an axial direction A, a radial direction R, and / or a circumferential direction C (e.g., into an axial slot or opening, a radial slot or opening, and / or a circumferential slot or opening).

[0043] An important term in this disclosure is "profile". The profile is the range of variation between the measured points on the airfoil surface and the ideal positions listed in Table I. The actual profile on a manufactured compressor stator vane will be different from those in Table I, and the design is robust to such variations, meaning that mechanical and aerodynamic functions are not impaired. As described above, a profile tolerance of +5% or -5% is used herein. The X, Y, and Z values are dimensionless values with respect to a scaling factor.

[0044] Any cross-section of the airfoil 100 of the stator vane 50 intercepted between the platform 114 or root 112 and the radial tip 116 (such as Figure 4 the cross-section shown) has a nominal profile. The "nominal profile" is the range of variation between the measured points on the airfoil surface and the ideal positions listed in Table I. The actual profile on a manufactured compressor blade can be different from those in Table I (e.g., due to manufacturing tolerances), and the design is robust to such variations, meaning that mechanical and aerodynamic functions are not impaired.

[0045] The Cartesian coordinate values of X, Y, and Z provided in Table I are dimensionless values that can be scaled by a scaling factor, as measured in any given unit of distance (e.g., inches). For example, the X, Y, and Z values in Table I are listed in dimensionless units and thus can use various dimensional units when these values are appropriately scaled by the scaling factor. As just one example, by multiplying the X, Y, and Z values by the scaling factor, the Cartesian coordinate values of X, Y, and Z can be converted into dimensional distances. The scaling factor can be substantially equal to 1, greater than 1, or less than 1. The scaling factor used to convert dimensionless values to dimensional distances can be a fraction (e.g., 1 / 2, 1 / 4, etc.), a decimal (e.g., 0.5, 1.5, 10.25, etc.), an integer (e.g., 1, 2, 10, 100, etc.), or a mixed fraction (e.g., 1 1 / 2, 10 1 / 4, etc.). The scaling factor can be a dimensional distance in any suitable format (e.g., inches, feet, millimeters, centimeters, etc.). In various embodiments, the scaling factor can be between about 0.01 inches and about 10 inches, or such as between about 0.02 inches and about 5 inches, or such as between about

[0046] In various embodiments, the X, Y, and Z values in Table I can be scaled as a function of the same scaling factor (e.g., a constant or a number) to provide a scaled-up or scaled-down airfoil. In this way, Table I defines the relationship between the corresponding X, Y, and Z coordinate values without specifying the unit of measurement (e.g., dimensional unit) for the various embodiments of the airfoil 100. Thus, while different scaling factors can be applied to the corresponding X, Y, and Z coordinate values of Table I to define different embodiments of the airfoil 100, each embodiment of the airfoil 100 is considered to be defined by the corresponding X, Y, and Z coordinate values of Table I regardless of the specific scaling factor.

[0047] The gas turbine hot gas path requires airfoils that meet the system requirements of aerodynamics and mechanical blade loading and efficiency. To define the airfoil shape of each compressor stator vane airfoil, there is a unique set of points or a locus of points in space that meet the stage requirements and can be manufactured. This unique locus of points meets the requirements of stage efficiency and is achieved through an iteration between aerodynamic loading and mechanical loading, enabling the turbine to operate in an efficient, safe, and smooth manner. These points are unique and specific to the system.

[0048] The locus defining the compressor stator vane airfoil shape includes a set of points having X, Y, and Z dimensions with respect to a reference origin coordinate system. The Cartesian coordinate system of the X, Y, and Z values given in Table I below defines the airfoil shape (which includes the respective airfoil profile sections) at various positions along its height (or along the span direction 118) of the airfoil belonging to one or more compressor stators.

[0049] Table I lists data for uncoated airfoils at cryogenic or room temperature. As used herein, the phrase "substantially according to the Cartesian coordinate values of X, Y, and Z listed in Table I" means that the envelope / tolerance of the coordinates is about + / - 5% in a direction perpendicular to any airfoil surface position and / or about + / - 5% of the chord 110 in a direction perpendicular to any airfoil surface position. In other words, the airfoil layout as embodied in the present disclosure is robust to this range of variation without compromising mechanical and aerodynamic functionality.

[0050] The point data origin 76 is defined at the base 114 of the airfoil 100. For example, the point data origin 76 may be defined at the root 112 of the airfoil 100. For example, in some embodiments, the point data origin 76 may be defined at the root 112 of the airfoil 100 at the intersection of a stack axis (e.g., a radially extending axis) and a compressed air flow path (e.g., an air flow path along the airfoil surface). The point data origin 76 corresponds to a dimensionless Z value equal to 0.

[0051] As described above, the Cartesian coordinate system has X, Y, and Z axes that are orthogonally related (e.g., mutually orthogonal), and the X axis is parallel to the axial centerline 23 of the shaft 22, i.e., the axis of rotation, and the positive X coordinate value is axially towards the rear of the gas turbine 10, i.e., the exhaust end. The positive Y coordinate value extends from the suction side surface 104 towards the pressure side surface 102, and the positive Z coordinate value is radially outward from the base 114 towards the radial tip 116 (e.g., radially inward with respect to the gas turbine coordinate system). All values in Table I are given at room temperature and do not include the corners 72 or coatings (not shown).

[0052] By defining X and Y coordinate values at selected positions in the Z direction perpendicular to the X, Y plane, the airfoil profile section 160 of the airfoil 100 of the stator vane 50 can be defined at each specified Z distance along the length of the airfoil 100. By connecting the X and Y values with smooth continuous arcs, each airfoil profile section of the airfoil 100 at each distance Z can be fixed. The complete airfoil shape 150 can be determined by smoothly connecting adjacent profile sections to each other.

[0053] The values in Table I are generated and displayed to three decimal places for determining the airfoil shape 150 of the airfoil 100. When the stator vane 50 is heated during operation of the gas turbine 10, surface stress and temperature will cause changes in the X, Y, and Z values. Thus, the values of the various airfoil profile sections given in Table I define the "nominal" airfoil profile, i.e., the profile of the uncoated airfoil under ambient, non-operating, or non-thermal conditions (e.g., room temperature).

[0054] In the actual profile of the airfoil 100, typical manufacturing tolerances and coatings must be considered. Each cross-section joins smoothly with the others to form a complete airfoil shape. Thus, it should be understood that the + / - typical manufacturing tolerances (i.e., the + / - values) include any coating thicknesses that are additional to the X and Y values given in Table I below. Thus, a distance of + / - 5% in a direction perpendicular to any surface location along the airfoil profile defines the airfoil profile envelope for this particular stator vane 50 airfoil design, i.e., the range of variation between the measurement points on the actual airfoil surface at nominal cryogenic or room temperature and the ideal locations of those points as given in Table I below at the same temperature. The data provided in Table I is scalable (i.e., by a uniform geometric scaling factor), and the geometry pertains to all aerodynamic scales equal to, above, and / or below 3000 RPM. The design of the airfoil 100 of the stator vane 50 is robust to this range of variation without compromising mechanical and aerodynamic functions.

[0055] The airfoil 100 can include various airfoil profile sections along the span direction 118. Each airfoil profile section in the airfoil profile sections can be "stacked" on top of one another along the Z direction such that when joined with a smooth continuous arc, a complete airfoil shape 150 can be determined. For example, for the common Cartesian coordinate values of Z in Table I, each airfoil profile section corresponds to the Cartesian coordinate values of X, Y, and Z. Additionally, for adjacent Cartesian coordinate values of Z in Table I, adjacent airfoil profile sections correspond to the Cartesian coordinate values of X, Y, and Z.

[0056] For example, Figure 4 illustrates an airfoil profile section 160 of the airfoil 100 taken along line 4-4 as shown in Figure 3 which can represent the airfoil profile section of the airfoil 100 at any spanwise location. It should be understood that the airfoil shape 150 of the airfoil 100 can vary or change at each spanwise location (or at each corresponding Z value). In this way, different airfoil profile sections 160 can be defined at each location (or at each Z value) along the span direction 118 of the airfoil 100. The airfoil profile sections 160 at each spanwise location (e.g., each Z value) of the airfoil 100 are joined together with a smooth continuous line, thereby defining the complete airfoil shape 150 of the airfoil 100.

[0057] The X, Y, and Z values of the Cartesian coordinate system given in Table I define the corresponding suction side surface or profile 104 and pressure side surface or profile 102 of the respective airfoil 100 at various locations along the span direction 118 of the respective airfoil 100. For example, in each of Table I, points 113 to 168 define along the Figure 3The corresponding suction side surface 104 and pressure side surface 102 of the corresponding airfoil intercepted at the Z value where the line 4-4 shown coincides.

[0058] By defining X coordinate values and Y coordinate values at selected positions in the Z direction perpendicular to the X-Y plane, an airfoil profile section 160 of the airfoil 100 can be obtained at each selected Z value position in the selected Z value positions (e.g., by connecting each X coordinate value and Y coordinate value at a given Z value to adjacent X coordinate values and Y coordinate values at the same Z value with a smooth continuous arc). At each Z value or position, the suction side profile 104 can be joined to the pressure side profile or surface 102, as Figure 4 shown, to define the airfoil profile section 160. The airfoil shape 150 of the airfoil 100 can be determined by smoothly connecting adjacent (e.g., "stacked") airfoil profile sections 160 to each other with a smooth continuous arc.

[0059] The values in Table I below are all computer-generated and are shown to three decimal places. In some embodiments, any value having less than 3 decimal places can be shown with trailing zeros to obtain 3 decimal places. Additionally, in some embodiments and taking into account manufacturing constraints, the actual values used to form the airfoil 100 may be considered valid to less than three decimal places for determining the airfoil shape 150 of the airfoil 100.

[0060] As will be understood, there are typical manufacturing tolerances that can be considered in the airfoil shape 150. Thus, the X values, Y values, and Z values given in Table I are for the airfoil shape 150 of the nominal airfoil. Accordingly, it should be understood that typical manufacturing tolerances (e.g., ±5%) may be applied to these X values, Y values, and Z values, and airfoils 100 having profiles substantially consistent with these values include such tolerances.

[0061] As described above, and according to the values in Table I and within the tolerances explained above, airfoil 100 may also be coated to prevent corrosion, erosion, wear, and oxidation after the manufacture of airfoil 100. For example, the coated area may include one or more corrosion-resistant layers, erosion-resistant layers, wear-resistant layers, anti-oxidation layers, or oxidation-resistant layers, or any combination thereof. For example, in embodiments where the airfoil is measured in inches, a corrosion-resistant coating having an average thickness of 0.008 inches (0.20 mm), or between 0.001 inches and 0.1 inches (between 0.025 mm and 2.5 mm), or between 0.0001 inches and 1 inch or greater (between 0.0025 mm and 12.7 mm or greater) may be provided. For example, in certain embodiments, the coating may increase the X and Y values on the suction side or pressure side in Table I by no more than about 3.5 mm along the first suction portion, the first pressure portion, or both. It should be understood that additional anti-oxidation coatings, such as outer coatings, may be provided. The values provided in Table I do not include the coated area or coating of airfoil 100. In other words, these values correspond to the bare surface of airfoil 100. The coated area may include one or more coating layers, surface treatments, or combinations thereof on the bare surface of airfoil 100.

[0062] The following Table I includes Cartesian coordinate data of the airfoil shape 150 of airfoil 100, which may be incorporated into the compressor section 14 of gas turbine 10.

[0063] In an exemplary embodiment, the following Table I includes Cartesian coordinate data of the airfoil shape 150 of airfoil 100 of stator vane 50, which is disposed in the intermediate stage 62 of compressor section 14. Specifically, the following Table I includes Cartesian coordinate data of the airfoil shape 150 of airfoil 100 of stator vane 50, which is disposed in the seventh stage S7 of compressor section 14.

[0064] Table I

[0065]

[0066]

[0067]

[0068]

[0069]

[0070]

[0071]

[0072]

[0073]

[0074]

[0075]

[0076]

[0077]

[0078]

[0079]

[0080]

[0081]

[0082]

[0083]

[0084]

[0085]

[0086] It should also be understood that the airfoil 100 disclosed in Table I above can be geometrically scaled up or down for use in other similar turbine designs. Accordingly, the coordinate values listed in Table I can be scaled up or down such that the airfoil profile shape remains the same. The scaling pattern of the coordinates in Table I will be represented by the X, Y, and Z coordinate values, where the dimensionless X, Y, and Z coordinate values are converted to distance units (e.g., inches) and multiplied or divided by a constant.

[0087] As Figure 4 shown, each airfoil 100 can define a stagger angle α (alpha) measured between the chord line 110 and the axial direction A of the gas turbine 10. Specifically, the stagger angle α can be measured at the trailing edge 108 of the airfoil 100 between the chord line 110 of the airfoil 100 and the axial centerline 23 (or axis of rotation) of the gas turbine 10. The stagger angle α of each airfoil 100 disclosed herein can advantageously vary along the spanwise direction 118 (or radial direction R) according to a corresponding stagger angle distribution. The stagger angle distribution can be a set of stagger angles α at each spanwise position (or radial position) along the airfoil 100 of a given airfoil 100.

[0088] In many embodiments, each stage S1 - S12 of rotor blades 44 may include a unique stagger angle distribution such that the combined use of stages S1 - S12 of rotor blades 44 will result in an efficient compressor section 14. For example, each airfoil 100 of rotor blades 44 within the first stage S1 may have a first stagger angle distribution, each airfoil 100 of rotor blades 44 within the second stage S2 may have a second stagger angle distribution, and so on for each rotating stage (S1 - S12) of compressor section 14.

[0089] Similarly, each stage S1 - S12 of stator vanes 50 may include a unique stagger angle distribution such that the combined use of stages S1 - S12 of stator vanes 50 will result in an efficient compressor section 14. For example, each airfoil 100 of stator vanes 50 within the first stage S1 may have a first stagger angle distribution, each airfoil 100 of stator vanes 50 within the second stage S2 may have a second stagger angle distribution, and so on for each stationary stage (S1 - S12) of compressor section 14.

[0090] According to an embodiment of the present disclosure, Figure 5 A graph showing the stagger angle distribution is presented, which may pertain to one or more airfoils 100 within a specific stage (e.g., S1 - S12) of compressor section 14. Each graph in the graph may be in dimensionless units. Specifically, the y - axis shows the percentage along the span direction 118 (e.g., 0% span represents the inner diameter, and 100% span represents the outer diameter). For example, for rotor blades 44, 0% span may represent the base of airfoil 100, and 100% span may represent the tip of airfoil 100. For stator vanes 50, 0% span may represent the tip of airfoil 100, and 100% span may represent the base of airfoil 100. The x - axis shows the ratio between the stagger angle at a specific span - wise position and the mid - span stagger angle (e.g., at approximately 50% span).

[0091] Each stagger angle distribution in the stagger angle distribution is plotted within the range between 15% span and 85% span of the respective airfoil 100 to which it pertains (e.g., 0% - 15% span points and 85% - 100% span points are omitted). When implemented in airfoils 100 on rotor blades 44 and / or stator vanes 50 within compressor section 14, each stagger angle distribution advantageously improves the aerodynamic efficiency of airfoils 100 (and thus the entire compressor section 14) when compared to existing designs.

[0092] Specifically, Figure 5is a graph of the stagger angle distribution, which is plotted in the range of 15% to 85% of the span of the airfoil 100 of the stator vane 50 (i.e., the seventh-stage stator vane) belonging to the seventh stage S7. In some embodiments, all of the stator vanes 50 in the seventh stage S7 of the compressor section 14 may include an airfoil 100 having a profile defined by the X, Y, and Z coordinate values of Table I and a stagger angle distribution according to Figure 5 The stagger angle distribution shown in Figure 5 is plotted according to the points in Table II below.

[0093] Table II

[0094]

[0095] The disclosed airfoil shape optimizes the machine conditions and specifications and is specific to the machine conditions and specifications. It provides a unique profile to achieve: 1) the interaction between other stages in the compressor section 14; 2) aerodynamic efficiency; and 3) normalized aerodynamic and mechanical blade loading. The locus of the disclosed points defined in Table I allows the gas turbine 10 or any other suitable turbine to operate in an efficient, safe, and smooth manner. Also as mentioned, the disclosed airfoil 100 can be adapted to any scale as long as: 1) the interaction between other stages in the compressor section 14; 2) aerodynamic efficiency; and 3) normalized aerodynamic and mechanical blade loading are maintained in the scaled turbine.

[0096] Accordingly, the airfoil 100 described herein improves the overall efficiency of the gas turbine 10. The airfoil 100 also meets all aerodynamic and stress requirements. For example, the airfoil 100 of the stator vane 50 thus has a specific shape in order to meet the aerodynamic, mechanical, and heat transfer requirements in an effective and cost-effective manner.

[0097] This written description uses examples to disclose the invention, including the best mode, and also enables any person skilled in the art to practice the invention, including making and using any device or system and performing any combined method. The patentable scope of the invention is defined by the claims and may include other examples that occur to those skilled in the art. If these other examples include structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims, then these other examples are intended to be within the scope of the claims.

[0098] Other aspects of the invention are provided by the subject matter of the following clauses:

[0099] A stator vane, comprising: an airfoil having an airfoil shape with a nominal profile substantially according to the Cartesian coordinate values of X, Y, and Z listed in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at the base of the airfoil, wherein the Cartesian coordinate values of X, Y, and Z are dimensionless values that can be converted to a dimensional distance in distance units by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in distance units; and wherein the X and Y values are connected by smooth continuous arcs to define an airfoil profile section at each Z value, and the airfoil profile sections at the Z values are smoothly joined to each other to form a complete airfoil shape.

[0100] The stator vane according to any one of the preceding clauses, wherein the airfoil includes a stagger angle distribution according to Table II, each stagger angle in the stagger angle distribution being measured between the chord line of the airfoil and the axis of rotation of the airfoil.

[0101] The stator vane according to any one of the preceding clauses, wherein the stator vane forms part of an intermediate stage of a compressor section.

[0102] The stator vane according to any one of the preceding clauses, wherein the stator vane is a seventh-stage compressor stator vane.

[0103] The stator vane according to any one of the preceding clauses, wherein the airfoil shape lies within an envelope that is within + / - 5% of the chord length in a direction perpendicular to any airfoil surface location.

[0104] The stator vane according to any one of the preceding clauses, wherein the scaling factor is between about 0.01 inches and about 10 inches.

[0105] The stator vane according to any one of the preceding clauses, wherein the X, Y, and Z values are scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil.

[0106] A stator vane, comprising: an airfoil having a nominal suction side profile, the nominal suction side profile being substantially according to the suction side Cartesian coordinate values of X, Y, and Z listed in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at the base of the airfoil, wherein the Cartesian coordinate values of X, Y, and Z are dimensionless values that can be converted to a dimensional distance in distance units by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in distance units; and wherein when connected by a smooth continuous arc, the X values and Y values define a suction side profile cross-section at each Z value, and the suction side profile cross-sections at the Z values are smoothly joined to each other to form a complete airfoil suction side shape.

[0107] The stator vane according to any one of the preceding clauses, wherein the airfoil includes a stagger angle distribution according to Table II, each stagger angle in the stagger angle distribution being measured between the chord line of the airfoil and the axis of rotation of the airfoil.

[0108] The stator vane according to any one of the preceding clauses, wherein the stator vane forms part of an intermediate stage of a compressor section.

[0109] The stator vane according to any one of the preceding clauses, wherein the stator vane is a seventh stage compressor stator vane.

[0110] The stator vane according to any one of the preceding clauses, wherein the nominal suction side profile lies within an envelope that is + / - 5% of the chord length in a direction perpendicular to any airfoil surface location.

[0111] The stator vane according to any one of the preceding clauses, wherein the scaling factor is between about 0.01 inches and about 10 inches.

[0112] The stator vane according to any one of the preceding clauses, wherein the X values, Y values, and Z values are scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil.

[0113] A turbine, comprising: a compressor section; a turbine section located downstream of the compressor section; a combustion section located downstream of the compressor section and upstream of the turbine section; and stator vanes disposed within one of the compressor section or the turbine section, the stator vanes comprising: an airfoil having an airfoil shape with a nominal profile substantially according to the Cartesian coordinate values of X, Y, and Z listed in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at the base of the airfoil, wherein the Cartesian coordinate values of X, Y, and Z are dimensionless values that can be converted to a dimensional distance in distance units by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in distance units; and wherein the X and Y values define an airfoil profile section at each Z value when connected by a smooth continuous arc, and the airfoil profile sections at the Z values are smoothly joined to each other to form a complete airfoil shape.

[0114] The turbine according to any of the preceding clauses, wherein the airfoil comprises a stagger angle distribution according to Table II, each stagger angle in the stagger angle distribution being measured between the chord line of the airfoil and the axis of rotation of the airfoil.

Claims

1. A stator vane, comprising: An airfoil having an airfoil shape with a nominal profile substantially according to the Cartesian coordinate values of X, Y, and Z listed in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at the base of the airfoil, wherein the Cartesian coordinate values of X, Y, and Z are dimensionless values that can be converted to dimensional distances in distance units by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in distance units; and wherein the X and Y values are connected by smooth continuous arcs to define an airfoil profile section at each Z value, and the airfoil profile sections at the Z values are smoothly joined to each other to form a complete airfoil shape.

2. The stator vane according to claim 1, wherein the airfoil includes a stagger angle distribution according to Table II, each stagger angle in the stagger angle distribution being measured between the chord line of the airfoil and the axis of rotation of the airfoil.

3. The stator vane according to claim 1, wherein the stator vane forms part of an intermediate stage of a compressor section.

4. The stator vane according to claim 1, wherein the stator vane is a seventh-stage compressor stator vane.

5. The stator vane according to claim 1, wherein the airfoil shape lies within an envelope that is within + / - 5% of the chord length in a direction perpendicular to any airfoil surface location.

6. The stator vane according to claim 1, wherein the scaling factor is between about 0.01 inches and about 10 inches.

7. The stator vane according to claim 1, wherein the X, Y, and Z values are scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil.

8. A stator vane, comprising: An airfoil having a nominal suction side profile substantially according to the suction side Cartesian coordinate values of X, Y, and Z listed in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at the base of the airfoil, wherein the Cartesian coordinate values of X, Y, and Z are dimensionless values that can be converted to dimensional distances in distance units by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in distance units; and wherein when connected by smooth continuous arcs, the X and Y values define a suction side profile section at each Z value, and the suction side profile sections at the Z values are smoothly joined to each other to form a complete airfoil suction side shape.

9. The stator vane according to claim 8, wherein the airfoil includes a stagger angle distribution according to Table II, each stagger angle in the stagger angle distribution being measured between the chord line of the airfoil and the axis of rotation of the airfoil.

10. The stator vane according to claim 8, wherein the stator vane forms part of an intermediate stage of a compressor section.

11. The stator vane according to claim 8, wherein the stator vane is a seventh-stage compressor stator vane.

12. The stator vane according to claim 8, wherein the nominal suction side profile lies within an envelope that is + / - 5% of the chord length in a direction perpendicular to any airfoil surface location.

13. The stator vane according to claim 8, wherein the scaling factor is between about 0.01 inches and about 10 inches.

14. The stator vane according to claim 8, wherein the X, Y, and Z values are scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil.

15. A turbine, comprising: A compressor section; A turbine section located downstream of the compressor section; A combustion section located downstream of the compressor section and upstream of the turbine section; And A stator vane disposed within one of the compressor section or the turbine section, the stator vane comprising: An airfoil having an airfoil shape with a nominal profile substantially according to the Cartesian coordinate values of X, Y, and Z listed in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at the base of the airfoil, wherein the Cartesian coordinate values of X, Y, and Z are dimensionless values that can be converted to a dimensional distance in distance units by multiplying the Cartesian coordinate values of X, Y, and Z by the scaling factor of the airfoil in distance units; and wherein the X and Y values define an airfoil profile section at each Z value when connected by a smooth continuous arc, and the airfoil profile sections at the Z values are smoothly joined to each other to form a complete airfoil shape.

16. The turbine according to claim 15, wherein the airfoil includes a stagger angle distribution according to Table II, each stagger angle in the stagger angle distribution being measured between the chord line of the airfoil and the axis of rotation of the airfoil.

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