AIR GUIDE VANES OF A COMPRESSOR STATOR GUIDE VANE

Abstract

A stator vane includes an air deflector having an air deflector shape. The air deflector shape has a nominal profile substantially according to the Cartesian coordinate values ​​of X, Y, and Z listed in one of TABLE I and TABLE II. The Cartesian coordinate values ​​of X, Y, and Z are defined relative to a point data origin at a base of the air deflector profile. The Cartesian coordinate values ​​of X, Y, and Z are dimensionless values ​​convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a scaling factor of the air deflector in the unit of distance. The X and Y values ​​are connected by smooth, continuous arcs to define air deflector profile sections at each Z value. The air deflector profile sections at the Z values ​​are smoothly connected to each other, thus forming a complete air deflector shape.

Description

AREA

[0001] The present disclosure relates to an air baffle for a compressor stator vane positioned within a stage of a compressor section of a land-based gas turbine system, and more particularly relates to a shape defining a profile for an air baffle of a compressor stator vane. STATE OF THE ART

[0002] Some gas turbine or combined cycle gas and steam turbine power systems utilize turbomachinery in their design and operation. Generally, turbomachinery utilizes air deflectors (e.g., stator vanes or nozzles and rotor blades) that are exposed to fluid flows during operation. These air deflectors are configured to aerodynamically interact with the fluid flows and transfer energy to or from those fluid flows as part of power generation. For example, the air deflectors may be used to compress fluid, generate thrust, convert kinetic energy to mechanical energy, and / or convert heat energy to mechanical energy. Due to these interactions and conversions, the aerodynamic characteristics of these air deflectors can result in losses that affect system and turbine operation, power capability, thrust, efficiency, and generated power. SHORT DESCRIPTION

[0003] Aspects and advantages of the stator vanes and turbomachines according to the present disclosure will be set forth in part in the description which follows, or will be apparent from the description, or may be learned through practice of the technology.

[0004] According to one embodiment, a stator vane is provided. A stator vane includes an air deflector having an air deflector shape. The air deflector shape has a nominal profile substantially according to the Cartesian coordinate values ​​of X, Y, and Z listed in one of TABLE I and TABLE II. The Cartesian coordinate values ​​of X, Y, and Z are defined relative to a point data origin at a base of the air deflector profile. The Cartesian coordinate values ​​of X, Y, and Z are dimensionless values ​​convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a scaling factor of the air deflector in the unit of distance. The X and Y values ​​are connected by smooth, continuous arcs to define air deflector profile sections at each Z value.The air baffle profile sections at the Z-values ​​are smoothly connected to each other, thus forming a complete air baffle shape.

[0005] According to another embodiment, a stator vane is provided. The stator vane includes an air baffle having a nominal suction side profile substantially according to the Cartesian suction side coordinate values ​​of X, Y, and Z listed in one of TABLE I or TABLE II. The Cartesian coordinate values ​​of X, Y, and Z are defined relative to a point data origin at a base of the air baffle profile. The Cartesian coordinate values ​​of X, Y, and Z are dimensionless values ​​convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a scaling factor of the air baffle in the unit of distance. The X and Y values ​​are connected by smooth, continuous arcs, thus defining suction side profile sections at each Z value.The suction side profile sections at the Z-values ​​are smoothly connected to each other, thus forming a complete suction side shape of the air baffle.

[0006] According to yet another embodiment, a turbomachine is provided. The turbomachine includes a compressor section, a turbine section upstream of the compressor section, and a combustion section upstream of the compressor section and downstream of the turbine section. A stator vane is positioned in one of the compressor section or the turbine section. The stator vane includes an air vane having an air vane shape. The air vane shape has a nominal profile substantially according to the Cartesian coordinate values ​​of X, Y, and Z listed in one of TABLE I and TABLE II. The Cartesian coordinate values ​​of X, Y, and Z are defined relative to a point data origin at a base of the air vane profile.The Cartesian coordinate values ​​of X, Y, and Z are dimensionless values ​​that can be converted into dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a vane scaling factor in the unit of distance. The X and Y values ​​are connected by smooth, continuous arcs to define vane profile sections at each Z value. The vane profile sections at the Z values ​​are smoothly connected to each other, thus forming a complete vane shape.

[0007] These and other features, aspects, and advantages of the present stator vanes and turbomachinery will be better understood by 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 and, together with the description, serve to explain the principles of the technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] A complete and further disclosure of the present stator vanes and turbomachinery, including the best mode of making and using the present systems and methods, directed to one of ordinary skill in the art, is set forth in the patent specification, which refers to the accompanying figures, in which: Fig.1 is a schematic illustration of a turbomachine according to embodiments of the present disclosure; Fig. 2 a cross-sectional side view of a compressor section (e.g. the turbomachine of Fig. 1) illustrated according to embodiments of the present disclosure; Fig. 3 is a perspective view of a stator vane as used in the compressor section of Fig. 2 may be used, according to embodiments of the present disclosure; Fig. 4 an air baffle profile section of an air baffle along the Fig. 3, according to embodiments of the present disclosure; Fig.5 illustrates a graph of a stagger angle distribution associated with an air baffle disposed on a stator vane within a particular stage of a compressor section, according to embodiments of the present disclosure; and Fig. 6 illustrates a graph of a stagger angle distribution associated with an air baffle disposed on a stator vane within a particular stage of a compressor section, according to embodiments of the present disclosure. DETAILED DESCRIPTION

[0009] Reference will now be made in detail to embodiments of the present stator vanes and turbomachines, one or more examples of which are illustrated in the drawings. Each example is provided to illustrate the technology, not to limit the technology. Indeed, it will be apparent to those skilled in the art that changes and variations may be made to the present technology without departing from the scope or spirit of the claimed technology. For example, features illustrated or described as part of one embodiment may be used with another embodiment to yield yet another embodiment. Thus, it is intended that the present disclosure cover such changes and variations as fall within the scope of the appended claims and their equivalents.

[0010] In the detailed description, numerical and letter designations are used to refer to features in the drawings. The same or similar designations in the drawings and description have been used to refer to the same or similar parts of the 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 location or importance of individual components.

[0011] As used herein, the terms "upstream" (or "front") and "downstream" (or "rear") refer to the relative direction with respect to fluid flow in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction in which the fluid is flowing. The term "radial" refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component, the term "axial" refers to the relative direction that is substantially parallel and / or coaxial with an axial centerline of a particular component, and the term "circumferential" refers to the relative direction that extends around the axial centerline of a particular component.

[0012] Approximate terms such as "generally," "substantially," or "about" include values ​​within ten percent greater or less than the stated value. When used in the context of an angle or direction, such terms include values ​​within ten degrees greater or less than the stated angle or direction. For example, "generally vertical" includes directions within ten degrees vertically in any direction, such as clockwise or counterclockwise.

[0013] With reference to the drawings Fig.1 is a schematic representation of a turbomachine, 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 an industrial and / or land-based gas turbine unless otherwise specified in the claims. For example, the stator vane air deflector described herein may be used in any type of turbomachine, including, but not limited to, a steam turbine, an aircraft gas turbine, or a marine gas turbine.

[0014] 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 combustors (not shown) within a combustor section 16 disposed downstream of the compressor section 14, a turbine section 18 disposed downstream of the combustion section 16, and an exhaust section 20 disposed downstream of the turbine section 18. Additionally, the gas turbine 10 may include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18.

[0015] The multi-stage axial compressor section, or compressor section 14, may generally include a plurality of rotor disks 24 (one of which is shown) and a plurality of rotor blades 44 extending radially outward from and connected to each rotor disk 24. Each rotor disk 24, in turn, may be coupled to, or form a portion of, the shaft 22 extending through the compressor section 14. The compressor section 14 may further include one or more stator vanes 50 disposed circumferentially around the shaft 22. The stator vanes 50 may be attached to a static casing, or compressor housing 48, that extends circumferentially around the rotor blades 44.

[0016] The turbine section 18 may generally include a plurality of rotor disks 28 (one of which is shown) and a plurality of rotor blades 30 extending radially outward from and connected to each rotor disk 28. Each rotor disk 28 may, in turn, be coupled to or form a portion of the shaft 22 extending through the turbine section 18. The turbine section 18 further includes a turbine housing 33 circumferentially surrounding 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 may be configured to support a plurality of stages of stationary nozzles 29 extending radially inward from the inner periphery of the turbine housing 33.

[0017] During operation, a working fluid, such as air, flows through the inlet section 12 and into the compressor section 14, where the air is progressively compressed, providing compressed air to the combustor(s) of the combustor section 16. The compressed air is mixed with fuel and burned within the combustor(s) to produce combustion gases 34. The combustion gases 34 flow through the hot gas path 32 from the combustor section 16 into the turbine section 18, where energy (kinetic and / or thermal) from the combustion gases 34 is transferred to the rotor blades 30, causing the shaft 22 to rotate. The rotational mechanical energy can then be used to power the compressor section 14 and / or generate electricity.The spent combustion gases 34 exiting the turbine section 18 (sometimes referred to as “flue gases” or “exhaust gases”) may then be exhausted from the gas turbine 10 via the exhaust section 20.

[0018] Fig. 2 illustrates a cross-sectional side view of an embodiment of the compressor section 14 of the gas turbine 10 of Fig. 1, shown as a multi-stage axial compressor section 14, according to embodiments of the present disclosure. As shown in the Fig. 1 and Fig. 2, the gas turbine 10 may define a cylindrical coordinate system. The cylindrical coordinate system may define an axial direction A (e.g., downstream direction) parallel to and / or along an 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.

[0019] In operation, air 15 may enter the compressor section 14 in the axial direction A through the inlet section 12 and may be pressurized in the multi-stage axial compressor section 14. The pressurized air may then be mixed with fuel for combustion in the combustor section 16 to drive the turbine section 18, which rotates the shaft 22 in the circumferential direction C and thus the multi-stage axial compressor section 14. The rotation of the shaft 22 also causes one or more rotor blades 44 (e.g., compressor rotor blades) within the multi-stage axial compressor section 14 to draw in and pressurize the air received from the inlet section 12.

[0020] The multi-stage axial compressor section 14 may include a rotor assembly 46 having a plurality of rotor disks 24. The rotor blades 44 may extend radially outward from the rotor disks 24. The entire rotor assembly 46 (e.g., rotor disks 24 and rotor blades 44) may rotate in the circumferential direction C during operation of the gas turbine 10. The rotor assembly 46 may be surrounded by a compressor housing 48. The compressor housing may 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) may extend radially inward from the compressor housing 48.

[0021] As in Fig.2, one or more stages of the stator vanes 50 may be variable stator vanes 51, such that an angle of the stator vane 50 may be selectively actuated (e.g., by a controller 200). For example, in the Fig. 2, the first two stages of the compressor section 14 (e.g., S1 and S2) may include variable stator vanes 51. In many embodiments, as shown, the rotor blades 44 and stator vanes 50 may be arranged in alternating stages such that most stages of the rotor blades 44 are arranged in axial direction A between two stages of stator vanes 50.

[0022] In some embodiments, the compressor housing 48 of the compressor section 14 or the inlet section 12 may include one or more sets of inlet guide vanes 52 (IGVs) (e.g., variable IGV stator vanes). The inlet guide vanes 52 may be mounted to the compressor housing 48, may be spaced apart from each other in the circumferential direction C, and may be operable to control the amount of air 15 entering the compressor section 14. Additionally, an outlet 56 of the compressor section 14 may include a set of outlet guide vanes 58 (OGVs). The OGVs 58 may be mounted to the compressor housing 48, may be spaced apart from each other in the circumferential direction C, and may be operable to control the amount of air 15 exiting the compressor section 14.

[0023] In examples such as Fig.2, the variable stator vanes 51 and the IGVs 52 may each be configured to vary their vane angle relative to the gas flow (e.g., air flow) by rotating the vane 51, 52 about a rotational axis (e.g., about the radially oriented vane shaft). However, each variable stator vane 51 (including the IGVs 52) may otherwise be stationary relative to the rotor blades 44. In certain embodiments, the variable stator vanes 51 and the IGVs 52 may be coupled to an actuator 19 (e.g., an electric drive, a pneumatic drive, or a hydraulic drive). The actuators 19 may be in operative communication (e.g., electrical communication) with a controller 200. The controller 200 may be operable to selectively vary the vane angle.In other embodiments, all of the stator vanes 50 may be fixed such that the stator vanes 50 are configured to maintain a fixed angular position (e.g., the vane angle does not change).

[0024] The compressor section 14 may include a plurality of rows or stages arranged in serial flow order, such as between 2 to 30, 2 to 25, 2 to 22, 2 to 14, or 2 to 10 rows or stages, or any specific number or range therebetween. Each stage may include a plurality of rotor blades 44 (attached to the rotor disks 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 multi-stage axial 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.In particular, the illustrated embodiment of the multi-stage axial compressor section 14 includes 22 stages (e.g., S1 to S22).

[0025] It should be understood that each stage includes 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, in each stage, the rotor blades 44 and stator vanes 50 are axially offset from one another such that the compressor section 14 includes an alternating arrangement of rotor blades 44 and stator vanes 50, one set after the other, along the length of the compressor section 14. Each set of rotor blades 44 extends (e.g., in a spaced-apart arrangement) in the circumferential direction C around the shaft 22, and each set of stator vanes 50 extends (e.g., in a spaced-apart arrangement) in the circumferential direction C within the compressor housing 48.

[0026] While the compressor section 14 may include more or fewer stages than illustrated, Fig.2 illustrates an embodiment of the compressor section 14 having twenty-two stages arranged in serial flow order and identified as follows: first stage S1, second stage S2, third stage S3, fourth stage S4, fifth stage S5, sixth stage S6, seventh stage S7, eighth stage S8, ninth stage S9, tenth stage S10, eleventh stage S11, twelfth stage S12, thirteenth stage S13, fourteenth stage S14, fifteenth stage S15, sixteenth stage S16, seventeenth stage S17, eighteenth stage S18, nineteenth stage S19, twentieth stage S20, twenty-first stage S21, and twenty-second stage S22. The IGVs 52 are located upstream (i.e., before) of the first stage S1, and the OGVs 58 are located downstream (i.e., after) of the twenty-second stage S22.

[0027] In certain embodiments, each stage may include rotor blades 44 and stator vanes 50 (e.g., fixed stator vanes 50 and / or variable stator vanes 51). As used herein, a rotor blade 44 positioned in any of sections S1 through S22 of compressor section 14 may be referred to by the stage in which it is positioned, e.g., "a first-stage compressor rotor blade," "a second-stage compressor rotor blade," "a third-stage compressor rotor blade," etc. Similarly, a stator vane 50 disposed in any of sections S1 through S22 of compressor section 14 may be referred to by the stage in which it is positioned, e.g., "a third-stage compressor stator vane," "a fourth-stage compressor stator vane," "a fifth-stage compressor stator vane," etc.

[0028] In operation, the rotor blades 44 may rotate circumferentially about the axial centerline 23 within the compressor housing 48 and between the stator vanes 50. The rotation of the rotor blades 44 may cause air to enter the inlet section 12. The air is then subsequently compressed as it traverses the various stages (e.g., first stage S1 through twenty-second stage S22) of the compressor section 14 and moves axially rearward from 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. As discussed above, the outlet 56 may include a set of exhaust guide vanes 58 (OGVs). The compressed air exiting the compressor section 14 may be directed to the combustor 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.

[0029] The IGV 52, the stages (e.g., S1 through S22) of the rotor blades 44 and stator vanes 50, and the OGV 58 of the compressor section 14 may be grouped into one or more sections of the compressor section 14 for reference purposes. For grouping purposes, sections 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, in serial flow order, an early stage 60, a mid-stage 62, and a late stage 64. In particular, the early stage 60 may include from about 0% to about 25% of the compressor section 14 (e.g., from the IGV 52 to about the sixth stage S6). The middle stage 62 may include from about 25% to about 75% of the compressor section 14 (e.g.,from about the seventh stage S7 to about the eighteenth stage S18). The late stage 64 may include from about 75% to about 100% of the compressor section 14 (e.g., from about the nineteenth stage S19 to the OGV 58).

[0030] Accordingly, the Cartesian coordinate data included in each of TABLES I and II may correspond to an air deflector shape of an air deflector 100 positioned in the middle stage 62 of the compressor section 14. In particular, the Cartesian coordinate data included in each of TABLES I and II may correspond to an air deflector shape of an air deflector 100 positioned within the last two stages of the middle stage 62 (e.g., the seventeenth stage S17 and the eighteenth stage S18).

[0031] For example, in embodiments, the Cartesian coordinate data contained in TABLE I may correspond to an air baffle shape of an air baffle 100 disposed on a stator vane 50 within the seventeenth stage S17 of the compressor section 14. The Cartesian coordinate data contained in TABLE II may correspond to an air baffle shape of an air baffle 100 disposed on a stator vane 50 within the eighteenth stage S18 of the compressor section 14.

[0032] However, in various other embodiments, each of TABLES I and II may contain Cartesian coordinate data of an airfoil shape of an airfoil 100 that may be disposed on a stator vane 50 or rotor blade 44 in any stage S1 through S22 of the compressor section 14. Accordingly, the airfoil shape defined by each of TABLES I and II should not be limited to a particular stage of the compressor section 14 unless expressly stated in the claims.

[0033] Fig. 3 shows a perspective view of a stator vane 50 that may be incorporated into any stage (e.g., S1 to S22) of the compressor section 14 according to embodiments of the present disclosure.

[0034] As shown, the stator vane 50 includes an air baffle 100 defining an air baffle shape 150. The air baffle 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 intersect at a leading edge 106 and a trailing edge 108 of the air baffle 100. A chord line 110 extends between the leading edge 106 and the trailing edge 108, so that the pressure and suction-side surfaces 102, 104 can be said to extend in the chord or chord direction between the leading edge 106 and the trailing edge 108. The leading and trailing edges, 106 and 108, respectively, can be described as parting or intersection lines between the suction side surface 104 and the pressure side surface 102.In other words, the suction side surface 104 and the pressure side surface 102 are coupled together along the leading edge 106 and the trailing edge 108, thereby defining an air vane-shaped cross-section that gradually changes in the longitudinal direction (or “spanwise direction”) along the air vane 100.

[0035] In operation, the stator vanes 50 may be stationary components that do not move in the circumferential direction C. For example, the stator vanes 50 may be coupled to and extend radially inward from the compressor casing 48. Each set (or stage) of stator vanes 50 within the compressor section 14 may be axially positioned between two sets (or stages) of rotor blades 44 that rotate in the circumferential direction C. For example, the rotor blades 44 rotate about the axial centerline 23 of the turbomachine and exert torque on a working fluid, such as air 15, thereby increasing the energy level of the fluid as the working fluid passes through the various stages S1 through S22 of the multi-stage axial compressor section 14 on its way to the combustor section 16. The stator vanes 50 may be adjacent (e.g., upstream and / or downstream) to the one or more sets of rotor blades 44.The stator vanes 50 decelerate the working fluid during rotation of the rotor blades 44, thereby converting a circumferential component of the working fluid flow's motion into pressure. Accordingly, the continuous rotation of the rotor blades 44 creates a continuous flow of compressed working fluid suitable for combustion by the combustor section 16.

[0036] As in Fig.3, the air baffle 100 includes a root or first end 112 that intersects and extends radially inward from a base or platform 114 of the stator vane 50. The air baffle 100 terminates radially at a second end or radial tip 116 of the air baffle 100. In some embodiments (not shown), the stator vane 50 may include a tip cover or tip platform that extends from the radial tip 116 generally parallel to the base 114. The pressure-side and suction-side surfaces 102, 104 may be said to extend spanwise or in the spanwise direction 118 between the root 112 and / or the platform 114 and the radial tip 116 of the air baffle 100.In other words, each stator vane 50 includes an air baffle 100 having opposed pressure-side and suction-side surfaces 102, 104 extending chordwise or chordwise 110 between opposed leading and trailing edges 106, 108 and extending spanwise or spanwise 118 between the root 112 and the radial tip 116 of the air baffle 100.

[0037] In certain configurations, the air baffle 100 may include a ledge 72 formed between the platform 114 and the air baffle 100 near the root 112. The ledge 72 may include a weld or solder ledge, which may be formed by conventional MIG welding, TIG welding, brazing, etc., and may include a profile that may reduce fluid dynamic losses due to the presence of the ledge 72. In certain embodiments, the platform 114, the air baffle 100, and the ledge 72 may 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 technology now known or later discovered and / or developed.

[0038] In various implementations, 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 projections, 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., in an axial slot or opening, a radial slot or opening, and / or a circumferential slot or opening).

[0039] An important term in this disclosure is "profile." Profile is the range of variation between measured points on an air vane surface and the ideal position listed in each of TABLES I and II. The actual profile of a manufactured compressor stator vane will differ from those in TABLES I and II, and the design is robust to these variations, meaning that mechanical and aerodynamic function are not compromised. As noted above, a profile tolerance of + or - 5% is used herein. The X, Y, and Z values ​​are all dimensionless relative to a scaling factor.

[0040] The air baffle 100 of the stator vane 50 has a nominal profile at each cross section between the platform 114 or root 112 and the radial tip 116, such as the profile shown in Fig.4. A "nominal profile" is the range of variation between measured points on an airfoil surface and the ideal position listed in Tables I and II. The actual profile of a manufactured compressor blade may differ from those in Tables I and II (e.g., due to manufacturing tolerances), and the design is robust to this variation, meaning that mechanical and aerodynamic function are not compromised.

[0041] The Cartesian coordinate values ​​of X, Y, and Z given in each of TABLES I and II are dimensionless values ​​that are scalable by a scaling factor, measured in any given distance unit (e.g., inches). For example, the X, Y, and Z values ​​in each of TABLES I and II are given in dimensionless units, and therefore different dimensional units can be used if the values ​​are appropriately scaled by a scaling factor. As one example only, the Cartesian coordinate values ​​of X, Y, and Z may be convertible to dimensional distances by multiplying the X, Y, and Z values ​​by a scaling factor. The scaling factor may be substantially equal to 1, greater than 1, or less than 1. The scaling factor used to convert dimensionless values ​​into dimensional distances can be a fraction (e.g., ½, ¼, etc.), a decimal fraction (e.g., 0.5, 1.5, 10.25, etc.), an integer (e.g.,1, 2, 10, 100, etc.) or a mixed number (e.g., 1½, 10¼, etc.). The scale factor may be a dimensional distance in any suitable format (e.g., inches, feet, millimeters, centimeters, etc.). In various embodiments, the scale factor may 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 0.04 inches and about 2.5 inches, or such as between about 0.06 inches and about 1.5 inches.

[0042] In various embodiments, the X, Y, and Z values ​​in each of TABLES I and II may be scaled depending on the same scaling factor (e.g., constant or number) to provide a scaled-up or scaled-down air deflector. In some embodiments, the scaling factor may be different for each of TABLES I and II, such that each of TABLES I and II has a unique scaling factor. In this way, each of TABLES I and II defines the relationships between the respective X, Y, and Z coordinate values ​​without specifying the units of measurement (e.g., dimensional units) for the various embodiments of the air deflector 100.Accordingly, although different scaling factors may be applied to the respective X, Y, and Z coordinate values ​​of each of TABLES I and II to define different embodiments of the air deflector 100, each embodiment of the air deflector 100 is considered to be defined by the respective X, Y, and Z coordinate values ​​of TABLES I and II regardless of the respective scaling factor. For example, the X, Y, and Z coordinate values ​​of TABLES I and II may each define an embodiment of the air deflector 100 formed with a 1:1 inch scale factor, a 1:2 inch scale factor, or a 1:1 cm scale factor. It should be noted that any scaling factor may be used with the X, Y, and Z coordinate values ​​of each of TABLES I and II, according to the design considerations of a particular embodiment.

[0043] The hot gas path of a gas turbine requires air baffles that meet the system requirements for aerodynamic and mechanical blade loading and efficiency. To define the air baffle shape of each compressor stator vane air baffle, there is a unique set or location of points in the space that meet the stage requirements and can be manufactured. These unique locations of points satisfy the stage efficiency requirements and are achieved through iteration between aerodynamic and mechanical loading, enabling efficient, safe, and smooth operation of the turbine. These points are unique and system-specific.

[0044] The locations defining the vane shape of the compressor stator guide vane include a set of points with dimensions X, Y, and Z relative to a reference origin coordinate system. The Cartesian coordinate system of X, Y, and Z values ​​specified in each of TABLES I and II below defines the vane shapes (including the various vane profile sections) of an air vane associated with one or more compressor stator guide vanes at various locations along its height (or along the spanwise direction 118).

[0045] Each of TABLES I and II lists data for an uncoated air deflector at cold temperature or room temperature. As used herein, the phrase "substantially in accordance with the Cartesian coordinate values ​​of X, Y, and Z listed in one of TABLE I (or II)" refers to the envelope / tolerance for the coordinates being about + / -5% in a direction normal to any position on the air deflector surface and / or about + / -5% of chord 110 in a direction nominal to any position on the air deflector surface. In other words, the air deflector design as embodied by the disclosure is robust to this range of variation without compromising mechanical and aerodynamic functions.

[0046] A point data origin 76 is defined at the base 114 of the air baffle 100. For example, the point data origin 76 may be defined at the root 112 of the air baffle 100. For example, in some embodiments, the point data origin 76 may be defined at the root 112 of the air baffle 100 at the intersection of a stack axis (e.g., a radial axis) and the compressed air flow path (e.g., a flow path of air along the surface of the air baffle). The point data origin 76 corresponds to the dimensionless Z value equal to 0.

[0047] As described above, the Cartesian coordinate system has mutually orthogonal (i.e., mutually orthogonal) X, Y, and Z axes, and the X axis is parallel to an axial centerline 23 of the shaft 22, i.e., the axis of rotation, and a positive X coordinate value extends axially toward a rear end, i.e., exhaust end, of the gas turbine 10. The positive Y coordinate value extends in the direction from the pressure side surface 102 toward the suction side surface 104, and the positive Z coordinate value extends radially outward from the base 114 toward the radial tip 116 (e.g., opposite the radial direction of the gas turbine 10). All values ​​in each of TABLES I and II are given at room temperature and do not include the ledge 72 or coatings (not shown).

[0048] By defining X and Y coordinate values ​​at selected positions in a Z direction normal to the XY plane, an 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 can be fixed at each Z distance. By smoothly connecting the adjacent profile sections together, the complete airfoil shape 150 can be determined.

[0049] The values ​​of TABLES I and II are generated and displayed to three decimal places to determine the vane shape 150 of the vane 100. As the stator vane 50 heats up during operation of the gas turbine 10, surface tension and temperature cause the X, Y, and Z values ​​to change. Accordingly, the values ​​given in TABLES I and II for the various vane profile sections define the "nominal" vane profile, that is, the profile of an uncoated vane at ambient, off-line, or non-hot conditions (e.g., room temperature).

[0050] There are typical manufacturing tolerances as well as coatings that must be taken into account in the actual profile of the air baffle 100. Each cross-section is smoothly connected to the other cross-sections to form the complete air baffle shape. It should therefore be noted that typical + / - manufacturing tolerances, i.e., + / - values ​​including any coating thicknesses, are added to the X and Y values ​​given in each of TABLES I and II below. Accordingly, a margin of + / - 5% in a direction normal to any surface position along the air baffle profile defines an air baffle profile envelope for this particular air baffle design of stator vane 50, i.e.,a range of variation between measured points on the actual air baffle surface at nominal cold or room temperature and the ideal position of these points, as specified in each of TABLES I and II below, at the same temperature. The data provided in each of TABLES I and II is scalable (i.e., by a uniform geometric scaling factor), and the geometry relates to all aerodynamic scales at, above, and / or below 3000 rpm. The design of the air baffle 100 for stator vane 50 is robust over this range of variation, without compromising mechanical and aerodynamic functions.

[0051] The air deflector 100 may include various air deflector profile sections along the spanwise direction 118. The individual air deflector profile sections may be "stacked" on top of one another along the Z direction such that, when connected with smooth, continuous arcs, the complete air deflector shape 150 may be determined. For example, each air deflector profile section corresponds to Cartesian coordinate values ​​of X, Y, and Z for a common Cartesian coordinate value of Z in each of TABLES I and II. Furthermore, adjacent air deflector profile sections correspond to the Cartesian coordinate values ​​of X, Y, and Z for adjacent Cartesian coordinate values ​​of Z in each of TABLES I and II.

[0052] For example, Fig. 4 an air baffle profile section 160 of an air baffle 100 along the Fig.3, which may be representative of a vane profile section of the air vane 100 at any spanwise position, according to embodiments of the present disclosure. It should be understood that the vane shape 150 of the air vane 100 may change or vary at each spanwise position (or at each respective Z-value). In this way, a different vane profile section 160 may be defined at each position along the spanwise direction 118 (or at each Z-value) of the air vane 100. The vane profile sections 160 at each spanwise position (e.g., at each Z-value) of the air vane 100 are connected by smooth, continuous lines, thereby defining the complete vane shape 150 of the air vane 100.

[0053] A Cartesian coordinate system of X, Y, and Z values ​​specified in each of TABLES I and II below defines respective suction side surfaces or profiles 104 and pressure side surfaces or profiles 102 of the respective air deflectors 100 at various locations along the spanwise direction 118 of the respective air deflectors 100. For example, in each of TABLES I and II, points 113 to 168 define the respective suction side surface 104 and pressure side surface 102 of a respective air deflector along the Z value associated with the Fig. 3 coincides with line 4-4.

[0054] By defining X and Y coordinate values ​​at selected positions in a Z direction normal to the XY plane, an air deflector profile section 160 of the air deflector 100 can be obtained at each of the selected Z value positions (e.g., by connecting each X and Y coordinate value at a given Z value to adjacent X and Y coordinate values ​​of the same Z value by smooth, continuous arcs). At each Z value or Z position, the suction side profile 104 can be connected to the pressure side profile or pressure side surface 102, as shown in Fig. 4 to define the air baffle profile section 160. The air baffle shape 150 of the air baffle 100 can be determined by smoothly connecting the adjacent (e.g., "stacked") air baffle profile sections 160 to one another by smooth, continuous arcs.

[0055] The values ​​in each of TABLES I and II below are computer-generated and are displayed to three decimal places. In certain embodiments, all values ​​with fewer than three decimal places may be displayed with trailing zeros to provide three decimal places. Furthermore, in some embodiments and in view of manufacturing constraints, actual values ​​useful for forming the air baffle 100 may be considered valid to fewer than three decimal places for determining the air baffle shape 150 of the air baffle 100.

[0056] It is understood that there are typical manufacturing tolerances that may be accommodated in the vane shape 150. Accordingly, the X, Y, and Z values ​​given in each of TABLES I and II refer to the vane shape 150 of a nominal vane. It is therefore understood that typical plus or minus manufacturing tolerances are applicable to these X, Y, and Z values, and that an air vane 100 having a profile substantially conforming to these values ​​will include such tolerances.

[0057] As previously mentioned, after the air baffle 100 is manufactured, the air baffle 100 may also be coated for protection against corrosion, erosion, wear, and oxidation, according to the values ​​in any of TABLES I and II and within the tolerances discussed above. For example, the coating area may include one or more corrosion-resistant layers, erosion-resistant layers, wear-resistant layers, oxidation-resistant or antioxidant layers, or any combination thereof. For example, in embodiments where the air baffle is measured in inches, a corrosion-resistant coating having an average thickness of 0.008 inches (0.20 mm), or between 0.001 and 0.1 inches (between 0.025 and 2.5 mm), or between 0.0001 and 1 inch or more (between 0.0025 and 12.7 mm or more) may be provided.For example, in certain embodiments, the coating may increase the X and Y values ​​of a suction side or a pressure side in either of TABLES I and II along a first suction section, a first pressure section, or both by no more than about 3.5 mm. It should be noted that additional antioxidant coatings, such as overcoats, may be provided. The values ​​provided in each of TABLES I and II exclude a coated area or coatings of the air baffle 100. In other words, these values ​​correspond to the bare surface of the air baffle 100. The coated area may include one or more coating layers, surface treatments, or a combination thereof over the bare surface of the air baffle 100.

[0058] TABLES I and II below each contain Cartesian coordinate data of an air baffle shape 150 of an air baffle 100 that may be integrated into the compressor section 14 of the gas turbine 10.

[0059] In exemplary embodiments, TABLE I below contains Cartesian coordinate data of an air baffle shape 150 of an air baffle 100 of a stator guide vane 50 arranged in the middle stage 62 of the compressor section 14. In particular, TABLE I below contains Cartesian coordinate data of an air baffle shape 150 of an air baffle 100 of a stator guide vane 50 arranged in the seventeenth stage S 17 of the compressor section 14. TABLE I PRINT PAGE SUCTION SIDE N X Y Z X Y Z 1 -0,530 -0,665 -0,006 0,743 0,672 -0,006 2 -0,529 -0,665 -0,006 0,742 0,673 -0,006 3 -0,528 -0,665 -0,006 0,742 0,674 -0,006 4 -0,527 -0,665 -0,006 0,740 0,676 -0,006 5 -0,524 -0,664 -0,006 0,737 0,678 -0,006 6 -0,520 -0,661 -0,006 0,730 0,679 -0,006 7 -0,515 -0,655 -0,006 0,722 0,676 -0,006 8 -0,508 -0,646 -0,006 0,711 0,672 -0,006 9 -0,502 -0,632 -0,006 0,696 0,666 -0,006 10 -0,494 -0,615 -0,006 0,677 0,659 -0,006 11 -0,485 -0,592 -0,006 0,653 0,649 -0,006 12 -0,474 -0,566 -0,006 0,625 0,638 -0,006 13 -0,462 -0,538 -0,006 0,595 0,626 -0,006 14 -0,448 -0,507 -0,006 0,563 0,614 -0,006 15 -0,432 -0,473 -0,006 0,528 0,600 -0,006 16 -0,413 -0,436 -0,006 0,487 0,583 -0,006 17 -0,393 -0,398 -0,006 0,445 0,565 -0,006 18 -0,371 -0,358 -0,006 0,401 0,546 -0,006 19 -0,347 -0,317 -0,006 0,355 0,526 -0,006 20 -0,321 -0,276 -0,006 0,308 0,504 -0,006 21 -0,293 -0,234 -0,006 0,259 0,480 -0,006 22 -0,262 -0,191 -0,006 0,209 0,455 -0,006 23 -0,229 -0,147 -0,006 0,158 0,427 -0,006 24 -0,193 -0,103 -0,006 0,106 0,397 -0,006 25 -0,156 -0,060 -0,006 0,055 0,365 -0,006 26 -0,119 -0,018 -0,006 0,006 0,331 -0,006 27 -0,080 0,024 -0,006 -0,043 0,296 -0,006 28 -0,041 0,065 -0,006 -0,090 0,259 -0,006 29 -0,002 0,105 -0,006 -0,135 0,219 -0,006 30 0,038 0,145 -0,006 -0,178 0,177 -0,006 31 0,079 0,185 -0,006 -0,219 0,133 -0,006 32 0,120 0,223 -0,006 -0,258 0,087 -0,006 33 0,162 0,261 -0,006 -0,293 0,039 -0,006 34 0,205 0,298 -0,006 -0,327 -0,011 -0,006 35 0,249 0,334 -0,006 -0,358 -0,063 -0,006 36 0,292 0,367 -0,006 -0,385 -0,114 -0,006 37 0,335 0,399 -0,006 -0,409 -0,164 -0,006 38 0,376 0,429 -0,006 -0,431 -0,214 -0,006 39 0,416 0,457 -0,006 -0,450 -0,262 -0,006 40 0,456 0,483 -0,006 -0,467 -0,309 -0,006 41 0,493 0,508 -0,006 -0,482 -0,355 -0,006 42 0,530 0,531 -0,006 -0,495 -0,399 -0,006 43 0,565 0,553 -0,006 -0,507 -0,442 -0,006 44 0,596 0,572 -0,006 -0,517 -0,480 -0,006 45 0,623 0,589 -0,006 -0,525 -0,516 -0,006 46 0,649 0,604 -0,006 -0,532 -0,547 -0,006 47 0,673 0,619 -0,006 -0,538 -0,576 -0,006 48 0,694 0,631 -0,006 -0,542 -0,602 -0,006 49 0,711 0,641 -0,006 -0,543 -0,622 -0,006 50 0,723 0,649 -0,006 -0,543 -0,638 -0,006 51 0,733 0,655 -0,006 -0,541 -0,650 -0,006 52 0,740 0,659 -0,006 -0,538 -0,658 -0,006 53 0,743 0,665 -0,006 -0,535 -0,662 -0,006 54 0,744 0,669 -0,006 -0,532 -0,664 -0,006 55 0,743 0,671 -0,006 -0,531 -0,665 -0,006 56 0,743 0,672 -0,006 -0,530 -0,665 -0,006 57 -0,534 -0,632 0,057 0,737 0,644 0,057 58 -0,534 -0,632 0,057 0,737 0,645 0,057 59 -0,533 -0,632 0,057 0,737 0,646 0,057 60 -0,532 -0,632 0,057 0,735 0,647 0,057 61 -0,529 -0,632 0,057 0,732 0,650 0,057 62 -0,525 -0,629 0,057 0,725 0,651 0,057 63 -0,519 -0,623 0,057 0,717 0,648 0,057 64 -0,513 -0,614 0,057 0,706 0,644 0,057 65 -0,505 -0,602 0,057 0,692 0,638 0,057 66 -0,497 -0,585 0,057 0,673 0,631 0,057 67 -0,487 -0,564 0,057 0,650 0,622 0,057 68 -0,475 -0,539 0,057 0,623 0,612 0,057 69 -0,462 -0,513 0,057 0,594 0,600 0,057 70 -0,447 -0,483 0,057 0,563 0,588 0,057 71 -0,429 -0,451 0,057 0,529 0,575 0,057 72 -0,409 -0,416 0,057 0,489 0,559 0,057 73 -0,387 -0,380 0,057 0,448 0,541 0,057 74 -0,364 -0,343 0,057 0,405 0,523 0,057 75 -0,338 -0,304 0,057 0,360 0,503 0,057 76 -0,311 -0,265 0,057 0,314 0,482 0,057 77 -0,281 -0,226 0,057 0,267 0,460 0,057 78 -0,250 -0,185 0,057 0,218 0,435 0,057 79 -0,216 -0,144 0,057 0,168 0,409 0,057 80 -0,180 -0,102 0,057 0,118 0,380 0,057 81 -0,144 -0,061 0,057 0,068 0,350 0,057 82 -0, 106 -0,021 0,057 0,019 0,318 0,057 83 -0,068 0,019 0,057 -0,029 0,285 0,057 84 -0,030 0,059 0,057 -0,076 0,249 0,057 85 0,009 0,097 0,057 -0,120 0,212 0,057 86 0,049 0,136 0,057 -0,163 0,173 0,057 87 0,089 0,174 0,057 -0,204 0,131 0,057 88 0,130 0,211 0,057 -0,243 0,088 0,057 89 0,171 0,247 0,057 -0,280 0,042 0,057 90 0,213 0,282 0,057 -0,314 -0,005 0,057 91 0,256 0,316 0,057 -0,346 -0,054 0,057 92 0,299 0,349 0,057 -0,374 -0,103 0,057 93 0,340 0,379 0,057 -0,400 -0,151 0,057 94 0,380 0,408 0,057 -0,423 -0,198 0,057 95 0,420 0,435 0,057 -0,444 -0,244 0,057 96 0,458 0,461 0,057 -0,462 -0,289 0,057 97 0,495 0,485 0,057 -0,478 -0,333 0,057 98 0,530 0,507 0,057 -0,493 -0,375 0,057 99 0,565 0,528 0,057 -0,506 -0,416 0,057 100 0,594 0,547 0,057 -0,517 -0,453 0,057 101 0,621 0,563 0,057 -0,526 -0,487 0,057 102 0,646 0,578 0,057 -0,533 -0,517 0,057 103 0,670 0,592 0,057 -0,540 -0,546 0,057 104 0,690 0,604 0,057 -0,544 -0,571 0,057 105 0,706 0,614 0,057 -0,547 -0,590 0,057 106 0,719 0,621 0,057 -0,547 -0,605 0,057 107 0,728 0,627 0,057 -0,545 -0,617 0,057 108 0,735 0,631 0,057 -0,542 -0,625 0,057 109 0,738 0,637 0,057 -0,539 -0,629 0,057 110 0,738 0,641 0,057 -0,537 -0,631 0,057 111 0,738 0,643 0,057 -0,535 -0,632 0,057 112 0,738 0,644 0,057 -0,535 -0,632 0,057 113 -0,541 -0,575 0,172 0,728 0,593 0,172 114 -0,541 -0,575 0,172 0,728 0,594 0,172 115 -0,540 -0,575 0,172 0,727 0,595 0,172 116 -0,539 -0,575 0,172 0,726 0,596 0,172 117 -0,536 -0,575 0,172 0,723 0,599 0,172 118 -0,532 -0,573 0,172 0,717 0,600 0,172 119 -0,526 -0,568 0,172 0,709 0,597 0,172 120 -0,519 -0,560 0,172 0,699 0,594 0,172 121 -0,511 -0,549 0,172 0,685 0,588 0,172 122 -0,501 -0,534 0,172 0,668 0,582 0,172 123 -0,490 -0,514 0,172 0,645 0,573 0,172 124 -0,476 -0,492 0,172 0,619 0,564 0,172 125 -0,461 -0,469 0,172 0,592 0,553 0,172 126 -0,443 -0,443 0,172 0,562 0,542 0,172 127 -0,423 -0,414 0,172 0,530 0,529 0,172 128 -0,401 -0,383 0,172 0,492 0,514 0,172 129 -0,377 -0,350 0,172 0,453 0,498 0,172 130 -0,351 -0,317 0,172 0,412 0,481 0,172 131 -0,324 -0,283 0,172 0,370 0,463 0,172 132 -0,294 -0,248 0,172 0,326 0,443 0,172 133 -0,264 -0,213 0,172 0,281 0,422 0,172 134 -0,231 -0,176 0,172 0,234 0,399 0,172 135 -0,196 -0,139 0,172 0,187 0,375 0,172 136 -0,160 -0,101 0,172 0,138 0,349 0,172 137 -0,124 -0,064 0,172 0,090 0,321 0,172 138 -0,086 -0,027 0,172 0,043 0,292 0,172 139 -0,049 0,010 0,172 -0,004 0,262 0,172 140 -0,011 0,046 0,172 -0,049 0,230 0,172 141 0,027 0,082 0,172 -0,093 0,197 0,172 142 0,066 0,117 0,172 -0,136 0,161 0,172 143 0,105 0,152 0,172 -0,177 0,124 0,172 144 0,145 0,186 0,172 -0,217 0,086 0,172 145 0,185 0,220 0,172 -0,254 0,045 0,172 146 0,226 0,253 0,172 -0,290 0,003 0,172 147 0,268 0,285 0,172 -0,324 -0,041 0,172 148 0,309 0,315 0,172 -0,355 -0,085 0,172 149 0,348 0,344 0,172 -0,382 -0,128 0,172 150 0,387 0,370 0,172 -0,408 -0,171 0,172 151 0,425 0,396 0,172 -0,431 -0,213 0,172 152 0,461 0,420 0,172 -0,451 -0,255 0,172 153 0,497 0,442 0,172 -0,470 -0,295 0,172 154 0,531 0,464 0,172 -0,486 -0,334 0,172 155 0,564 0,484 0,172 -0,501 -0,372 0,172 156 0,592 0,501 0,172 -0,514 -0,406 0,172 157 0,617 0,516 0,172 -0,525 -0,438 0,172 158 0,642 0,531 0,172 -0,534 -0,466 0,172 159 0,664 0,544 0,172 -0,542 -0,492 0,172 160 0,684 0,555 0,172 -0,548 -0,516 0,172 161 0,699 0,564 0,172 -0,551 -0,534 0,172 162 0,711 0,571 0,172 -0,551 -0,549 0,172 163 0,720 0,576 0,172 -0,550 -0,560 0,172 164 0,726 0,581 0,172 -0,548 -0,568 0,172 165 0,729 0,586 0,172 -0,546 -0,571 0,172 166 0,729 0,590 0,172 -0,543 -0,573 0,172 167 0,729 0,592 0,172 -0,542 -0,574 0,172 168 0,728 0,593 0,172 -0,542 -0,575 0,172 169 -0,550 -0,502 0,337 0,716 0,525 0,337 170 -0,550 -0,502 0,337 0,716 0,526 0,337 171 -0,549 -0,502 0,337 0,715 0,527 0,337 172 -0,548 -0,502 0,337 0,714 0,528 0,337 173 -0,545 -0,502 0,337 0,712 0,531 0,337 174 -0,541 -0,501 0,337 0,706 0,532 0,337 175 -0,535 -0,498 0,337 0,698 0,530 0,337 176 -0,527 -0,492 0,337 0,689 0,527 0,337 177 -0,518 -0,482 0,337 0,676 0,522 0,337 178 -0,507 -0,470 0,337 0,659 0,516 0,337 179 -0,493 -0,454 0,337 0,638 0,508 0,337 180 -0,477 -0,435 0,337 0,614 0,499 0,337 181 -0,460 -0,415 0,337 0,588 0,490 0,337 182 -0,440 -0,393 0,337 0,561 0,479 0,337 183 -0,418 -0,369 0,337 0,530 0,468 0,337 184 -0,393 -0,342 0,337 0,495 0,454 0,337 185 -0,367 -0,315 0,337 0,458 0,439 0,337 186 -0,339 -0,287 0,337 0,420 0,424 0,337 187 -0,310 -0,258 0,337 0,380 0,407 0,337 188 -0,280 -0,228 0,337 0,339 0,389 0,337 189 -0,248 -0,197 0,337 0,297 0,370 0,337 190 -0,214 -0,166 0,337 0,253 0,350 0,337 191 -0,179 -0,133 0,337 0,208 0,328 0,337 192 -0,143 -0,100 0,337 0,162 0,305 0,337 193 -0, 106 -0,067 0,337 0,116 0,281 0,337 194 -0,069 -0,034 0,337 0,071 0,256 0,337 195 -0,032 -0,002 0,337 0,027 0,229 0,337 196 0,006 0,031 0,337 -0,017 0,202 0,337 197 0,043 0,063 0,337 -0,060 0,173 0,337 198 0,081 0,094 0,337 -0,102 0,143 0,337 199 0,120 0,125 0,337 -0,143 0,112 0,337 200 0,159 0,156 0,337 -0,183 0,079 0,337 201 0,198 0,185 0,337 -0,222 0,045 0,337 202 0,237 0,215 0,337 -0,259 0,009 0,337 203 0,277 0,244 0,337 -0,295 -0,029 0,337 204 0,317 0,271 0,337 -0,328 -0,066 0,337 205 0,355 0,297 0,337 -0,358 -0,104 0,337 206 0,392 0,321 0,337 -0,386 -0,141 0,337 207 0,428 0,345 0,337 -0,412 -0,177 0,337 208 0,463 0,366 0,337 -0,435 -0,214 0,337 209 0,496 0,387 0,337 -0,456 -0,249 0,337 210 0,529 0,406 0,337 -0,476 -0,283 0,337 211 0,560 0,425 0,337 -0,494 -0,317 0,337 212 0,587 0,441 0,337 -0,509 -0,348 0,337 213 0,611 0,454 0,337 -0,522 -0,376 0,337 214 0,634 0,468 0,337 -0,533 -0,401 0,337 215 0,656 0,480 0,337 -0,543 -0,425 0,337 216 0,674 0,490 0,337 -0,551 -0,446 0,337 217 0,689 0,498 0,337 -0,555 -0,463 0,337 218 0,700 0,505 0,337 -0,557 -0,476 0,337 219 0,709 0,509 0,337 -0,557 -0,487 0,337 220 0,715 0,514 0,337 -0,556 -0,494 0,337 221 0,717 0,519 0,337 -0,554 -0,498 0,337 222 0,717 0,522 0,337 -0,552 -0,500 0,337 223 0,716 0,524 0,337 -0,551 -0,501 0,337 224 0,716 0,525 0,337 -0,551 -0,502 0,337 225 -0,552 -0,458 0,463 0,707 0,485 0,463 226 -0,552 -0,459 0,463 0,707 0,486 0,463 227 -0,551 -0,459 0,463 0,707 0,487 0,463 228 -0,550 -0,459 0,463 0,705 0,488 0,463 229 -0,547 -0,460 0,463 0,703 0,490 0,463 230 -0,543 -0,459 0,463 0,697 0,492 0,463 231 -0,537 -0,456 0,463 0,690 0,490 0,463 232 -0,529 -0,451 0,463 0,681 0,487 0,463 233 -0,519 -0,443 0,463 0,669 0,482 0,463 234 -0,507 -0,432 0,463 0,653 0,477 0,463 235 -0,492 -0,418 0,463 0,633 0,469 0,463 236 -0,475 -0,401 0,463 0,610 0,461 0,463 237 -0,457 -0,384 0,463 0,585 0,451 0,463 238 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0,575 1,798 620 -0,580 -0,425 1,798 0,591 0,576 1,798 621 -0,578 -0,425 1,798 0,589 0,578 1,798 622 -0,574 -0,423 1,798 0,583 0,578 1,798 623 -0,568 -0,420 1,798 0,577 0,576 1,798 624 -0,561 -0,414 1,798 0,568 0,572 1,798 625 -0,552 -0,405 1,798 0,556 0,568 1,798 626 -0,541 -0,394 1,798 0,541 0,562 1,798 627 -0,528 -0,378 1,798 0,521 0,554 1,798 628 -0,513 -0,360 1,798 0,499 0,545 1,798 629 -0,498 -0,341 1,798 0,476 0,535 1,798 630 -0,480 -0,319 1,798 0,451 0,524 1,798 631 -0,460 -0,295 1,798 0,423 0,512 1,798 632 -0,438 -0,269 1,798 0,391 0,497 1,798 633 -0,415 -0,242 1,798 0,358 0,481 1,798 634 -0,390 -0,214 1,798 0,323 0,464 1,798 635 -0,364 -0,184 1,798 0,288 0,446 1,798 636 -0,337 -0,155 1,798 0,251 0,427 1,798 637 -0,308 -0,124 1,798 0,213 0,406 1,798 638 -0,278 -0,092 1,798 0,175 0,383 1,798 639 -0,246 -0,060 1,798 0,135 0,360 1,798 640 -0,213 -0,027 1,798 0,094 0,334 1,798 641 -0,180 0,006 1,798 0,054 0,308 1,798 642 -0,146 0,038 1,798 0,014 0,282 1,798 643 -0,112 0,070 1,798 -0,025 0,254 1,798 644 -0,077 0,102 1,798 -0,064 0,226 1,798 645 -0,042 0,133 1,798 -0,102 0,196 1,798 646 -0,007 0,164 1,798 -0,139 0,165 1,798 647 0,028 0,194 1,798 -0,175 0,134 1,798 648 0,064 0,224 1,798 -0,210 0,101 1,798 649 0,100 0,254 1,798 -0,245 0,068 1,798 650 0,137 0,282 1,798 -0,278 0,034 1,798 651 0,175 0,311 1,798 -0,311 -0,002 1,798 652 0,211 0,337 1,798 -0,342 -0,036 1,798 653 0,247 0,362 1,798 -0,371 -0,070 1,798 654 0,282 0,386 1,798 -0,398 -0,104 1,798 655 0,316 0,408 1,798 -0,423 -0,137 1,798 656 0,349 0,429 1,798 -0,447 -0,169 1,798 657 0,380 0,449 1,798 -0,470 -0,200 1,798 658 0,411 0,467 1,798 -0,491 -0,230 1,798 659 0,441 0,484 1,798 -0,510 -0,259 1,798 660 0,467 0,499 1,798 -0,528 -0,286 1,798 661 0,490 0,511 1,798 -0,543 -0,311 1,798 662 0,512 0,523 1,798 -0,556 -0,332 1,798 663 0,533 0,534 1,798 -0,567 -0,354 1,798 664 0,551 0,543 1,798 -0,576 -0,372 1,798 665 0,565 0,550 1,798 -0,582 -0,387 1,798 666 0,576 0,556 1,798 -0,585 -0,400 1,798 667 0,584 0,560 1,798 -0,586 -0,409 1,798 668 0,591 0,563 1,798 -0,586 -0,416 1,798 669 0,594 0,567 1,798 -0,585 -0,420 1,798 670 0,594 0,570 1,798 -0,584 -0,422 1,798 671 0,594 0,572 1,798 -0,583 -0,423 1,798 672 0,593 0,573 1,798 -0,582 -0,424 1,798 673 -0,593 -0,441 1,929 0,554 0,609 1,929 674 -0,593 -0,441 1,929 0,553 0,609 1,929 675 -0,593 -0,441 1,929 0,553 0,610 1,929 676 -0,591 -0,441 1,929 0,552 0,611 1,929 677 -0,589 -0,441 1,929 0,549 0,613 1,929 678 -0,585 -0,439 1,929 0,544 0,614 1,929 679 -0,579 -0,435 1,929 0,537 0,611 1,929 680 -0,572 -0,429 1,929 0,528 0,608 1,929 681 -0,564 -0,420 1,929 0,516 0,603 1,929 682 -0,554 -0,407 1,929 0,500 0,597 1,929 683 -0,542 -0,390 1,929 0,481 0,590 1,929 684 -0,529 -0,371 1,929 0,458 0,581 1,929 685 -0,515 -0,350 1,929 0,434 0,571 1,929 686 -0,499 -0,327 1,929 0,409 0,560 1,929 687 -0,480 -0,301 1,929 0,381 0,547 1,929 688 -0,460 -0,273 1,929 0,348 0,532 1,929 689 -0,439 -0,244 1,929 0,315 0,516 1,929 690 -0,416 -0,213 1,929 0,280 0,499 1,929 691 -0,391 -0,182 1,929 0,244 0,480 1,929 692 -0,366 -0,150 1,929 0,207 0,460 1,929 693 -0,339 -0,117 1,929 0,169 0,438 1,929 694 -0,310 -0,084 1,929 0,130 0,415 1,929 695 -0,280 -0,049 1,929 0,090 0,390 1,929 696 -0,249 -0,014 1,929 0,049 0,363 1,929 697 -0,217 0,021 1,929 0,009 0,336 1,929 698 -0,184 0,055 1,929 -0,031 0,308 1,929 699 -0,151 0,089 1,929 -0,069 0,278 1,929 700 -0,117 0,122 1,929 -0,107 0,247 1,929 701 -0,083 0,155 1,929 -0,144 0,216 1,929 702 -0,049 0,187 1,929 -0,180 0,183 1,929 703 -0,014 0,219 1,929 -0,215 0,149 1,929 704 0,022 0,251 1,929 -0,249 0,114 1,929 705 0,058 0,281 1,929 -0,281 0,078 1,929 706 0,094 0,311 1,929 -0,313 0,041 1,929 707 0,131 0,341 1,929 -0,345 0,004 1,929 708 0,168 0,368 1,929 -0,374 -0,033 1,929 709 0,204 0,394 1,929 -0,401 -0,070 1,929 710 0,238 0,419 1,929 -0,427 -0,105 1,929 711 0,272 0,442 1,929 -0,451 -0,140 1,929 712 0,306 0,463 1,929 -0,473 -0,174 1,929 713 0,338 0,483 1,929 -0,494 -0,207 1,929 714 0,369 0,502 1,929 -0,513 -0,238 1,929 715 0,399 0,519 1,929 -0,531 -0,269 1,929 716 0,425 0,534 1,929 -0,547 -0,297 1,929 717 0,448 0,547 1,929 -0,561 -0,323 1,929 718 0,471 0,559 1,929 -0,573 -0,346 1,929 719 0,492 0,569 1,929 -0,583 -0,368 1,929 720 0,510 0,579 1,929 -0,591 -0,388 1,929 721 0,524 0,586 1,929 -0,595 -0,404 1,929 722 0,536 0,591 1,929 -0,598 -0,416 1,929 723 0,544 0,595 1,929 -0,599 -0,426 1,929 724 0,550 0,598 1,929 -0,598 -0,433 1,929 725 0,554 0,603 1,929 -0,597 -0,437 1,929 726 0,554 0,606 1,929 -0,595 -0,439 1,929 727 0,554 0,608 1,929 -0,594 -0,440 1,929 728 0,554 0,608 1,929 -0,594 -0,440 1,929 729 -0,604 -0,460 2,025 0,522 0,634 2,025 730 -0,604 -0,460 2,025 0,522 0,634 2,025 731 -0,603 -0,460 2,025 0,521 0,635 2,025 732 -0,602 -0,460 2,025 0,520 0,636 2,025 733 -0,599 -0,460 2,025 0,517 0,638 2,025 734 -0,596 -0,458 2,025 0,512 0,638 2,025 735 -0,590 -0,454 2,025 0,505 0,636 2,025 736 -0,583 -0,447 2,025 0,495 0,633 2,025 737 -0,576 -0,437 2,025 0,483 0,628 2,025 738 -0,567 -0,423 2,025 0,468 0,622 2,025 739 -0,556 -0,406 2,025 0,448 0,615 2,025 740 -0,544 -0,385 2,025 0,425 0,606 2,025 741 -0,531 -0,363 2,025 0,400 0,596 2,025 742 -0,516 -0,338 2,025 0,374 0,585 2,025 743 -0,500 -0,311 2,025 0,346 0,572 2,025 744 -0,481 -0,281 2,025 0,313 0,557 2,025 745 -0,461 -0,250 2,025 0,278 0,541 2,025 746 -0,440 -0,218 2,025 0,243 0,523 2,025 747 -0,417 -0,185 2,025 0,206 0,504 2,025 748 -0,393 -0,151 2,025 0,169 0,484 2,025 749 -0,368 -0,116 2,025 0,130 0,461 2,025 750 -0,341 -0,081 2,025 0,091 0,438 2,025 751 -0,312 -0,044 2,025 0,050 0,412 2,025 752 -0,282 -0,007 2,025 0,009 0,384 2,025 753 -0,251 0,029 2,025 -0,031 0,356 2,025 754 -0,219 0,065 2,025 -0,071 0,326 2,025 755 -0,186 0,100 2,025 -0,109 0,295 2,025 756 -0,153 0,135 2,025 -0,146 0,262 2,025 757 -0,120 0,169 2,025 -0,182 0,229 2,025 758 -0,085 0,203 2,025 -0,217 0,194 2,025 759 -0,051 0,236 2,025 -0,251 0,158 2,025 760 -0,015 0,268 2,025 -0,284 0,121 2,025 761 0,021 0,300 2,025 -0,316 0,083 2,025 762 0,057 0,331 2,025 -0,347 0,044 2,025 763 0,094 0,361 2,025 -0,377 0,004 2,025 764 0,131 0,390 2,025 -0,404 -0,034 2,025 765 0,167 0,417 2,025 -0,430 -0,073 2,025 766 0,202 0,442 2,025 -0,454 -0,110 2,025 767 0,236 0,465 2,025 -0,477 -0,147 2,025 768 0,270 0,487 2,025 -0,497 -0,182 2,025 769 0,302 0,507 2,025 -0,517 -0,217 2,025 770 0,334 0,526 2,025 -0,535 -0,250 2,025 771 0,364 0,544 2,025 -0,551 -0,282 2,025 772 0,391 0,559 2,025 -0,566 -0,312 2,025 773 0,415 0,572 2,025 -0,579 -0,339 2,025 774 0,437 0,583 2,025 -0,590 -0,363 2,025 775 0,459 0,594 2,025 -0,598 -0,386 2,025 776 0,477 0,604 2,025 -0,605 -0,406 2,025 777 0,492 0,611 2,025 -0,608 -0,422 2,025 778 0,503 0,616 2,025 -0,610 -0,435 2,025 779 0,512 0,620 2,025 -0,610 -0,445 2,025 780 0,518 0,623 2,025 -0,609 -0,453 2,025 781 0,522 0,627 2,025 -0,608 -0,456 2,025 782 0,523 0,630 2,025 -0,606 -0,459 2,025 783 0,522 0,632 2,025 -0,605 -0,459 2,025 784 0,522 0,633 2,025 -0,604 -0,460 2,025 785 -0,614 -0,482 2,122 0,488 0,656 2,122 786 -0,613 -0,482 2,122 0,487 0,657 2,122 787 -0,613 -0,482 2,122 0,487 0,658 2,122 788 -0,611 -0,482 2,122 0,486 0,659 2,122 789 -0,609 -0,481 2,122 0,483 0,661 2,122 790 -0,605 -0,479 2,122 0,477 0,661 2,122 791 -0,600 -0,474 2,122 0,470 0,658 2,122 792 -0,594 -0,467 2,122 0,461 0,655 2,122 793 -0,587 -0,456 2,122 0,448 0,651 2,122 794 -0,578 -0,442 2,122 0,432 0,645 2,122 795 -0,569 -0,423 2,122 0,412 0,637 2,122 796 -0,558 -0,401 2,122 0,388 0,629 2,122 797 -0,547 -0,378 2,122 0,363 0,619 2,122 798 -0,534 -0,352 2,122 0,337 0,608 2,122 799 -0,520 -0,323 2,122 0,307 0,595 2,122 800 -0,503 -0,291 2,122 0,274 0,581 2,122 801 -0,486 -0,258 2,122 0,239 0,564 2,122 802 -0,466 -0,224 2,122 0,202 0,547 2,122 803 -0,446 -0,189 2,122 0,165 0,528 2,122 804 -0,424 -0,154 2,122 0,127 0,507 2,122 805 -0,400 -0,117 2,122 0,087 0,484 2,122 806 -0,375 -0,079 2,122 0,047 0,460 2,122 807 -0,348 -0,041 2,122 0,006 0,434 2,122 808 -0,319 -0,002 2,122 -0,035 0,405 2,122 809 -0,289 0,037 2,122 -0,076 0,375 2,122 810 -0,258 0,074 2,122 -0,115 0,344 2,122 811 -0,226 0,111 2,122 -0,153 0,311 2,122 812 -0,193 0,147 2,122 -0,190 0,276 2,122 813 -0,160 0,182 2,122 -0,226 0,241 2,122 814 -0,126 0,217 2,122 -0,260 0,204 2,122 815 -0,091 0,251 2,122 -0,293 0,166 2,122 816 -0,056 0,285 2,122 -0,325 0,127 2,122 817 -0,020 0,317 2,122 -0,355 0,087 2,122 818 0,017 0,350 2,122 -0,385 0,046 2,122 819 0,054 0,381 2,122 -0,413 0,004 2,122 820 0,090 0,410 2,122 -0,439 -0,037 2,122 821 0,127 0,438 2,122 -0,463 -0,077 2,122 822 0,162 0,463 2,122 -0,485 -0,117 2,122 823 0,197 0,487 2,122 -0,506 -0,155 2,122 824 0,231 0,509 2,122 -0,525 -0,193 2,122 825 0,264 0,530 2,122 -0,542 -0,229 2,122 826 0,296 0,549 2,122 -0,558 -0,264 2,122 827 0,327 0,567 2,122 -0,573 -0,298 2,122 828 0,354 0,582 2,122 -0,586 -0,329 2,122 829 0,378 0,594 2,122 -0,597 -0,357 2,122 830 0,401 0,606 2,122 -0,606 -0,382 2,122 831 0,423 0,617 2,122 -0,613 -0,406 2,122 832 0,442 0,626 2,122 -0,618 -0,427 2,122 833 0,456 0,633 2,122 -0,620 -0,444 2,122 834 0,468 0,639 2,122 -0,621 -0,457 2,122 835 0,477 0,643 2,122 -0,621 -0,467 2,122 836 0,484 0,646 2,122 -0,619 -0,475 2,122 837 0,487 0,650 2,122 -0,617 -0,479 2,122 838 0,488 0,653 2,122 -0,616 -0,481 2,122 839 0,488 0,655 2,122 -0,614 -0,481 2,122 840 0,488 0,656 2,122 -0,614 -0,482 2,122

[0060] In exemplary embodiments, TABLE II below contains Cartesian coordinate data of an air baffle shape 150 of an air baffle 100 of a stator guide vane 50 arranged in the middle stage 62 of the compressor section 14. In particular, TABLE II below contains Cartesian coordinate data of an air baffle shape 150 of an air baffle 100 of a stator guide vane 50 arranged in the fourteenth stage S18 of the compressor section 14. TABLE II PRINT PAGE SUCTION SIDE N X Y Z X Y Z 1 -0,532 -0,788 -0,005 0,956 0,811 -0,005 2 -0,531 -0,788 -0,005 0,955 0,811 -0,005 3 -0,530 -0,788 -0,005 0,955 0,812 -0,005 4 -0,528 -0,788 -0,005 0,953 0,815 -0,005 5 -0,525 -0,787 -0,005 0,949 0,817 -0,005 6 -0,520 -0,784 -0,005 0,941 0,818 -0,005 7 -0,514 -0,776 -0,005 0,931 0,815 -0,005 8 -0,506 -0,766 -0,005 0,918 0,809 -0,005 9 -0,497 -0,750 -0,005 0,901 0,802 -0,005 10 -0,488 -0,730 -0,005 0,879 0,793 -0,005 11 -0,476 -0,703 -0,005 0,851 0,781 -0,005 12 -0,463 -0,673 -0,005 0,818 0,767 -0,005 13 -0,447 -0,641 -0,005 0,784 0,752 -0,005 14 -0,430 -0,605 -0,005 0,747 0,736 -0,005 15 -0,410 -0,565 -0,005 0,706 0,718 -0,005 16 -0,387 -0,522 -0,005 0,659 0,697 -0,005 17 -0,362 -0,478 -0,005 0,610 0,674 -0,005 18 -0,334 -0,432 -0,005 0,559 0,650 -0,005 19 -0,305 -0,385 -0,005 0,506 0,625 -0,005 20 -0,273 -0,336 -0,005 0,451 0,597 -0,005 21 -0,239 -0,287 -0,005 0,395 0,567 -0,005 22 -0,202 -0,237 -0,005 0,337 0,536 -0,005 23 -0,163 -0,186 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0,385 0,585 2,218 692 -0,336 -0,198 2,218 0,341 0,560 2,218 693 -0,303 -0,158 2,218 0,296 0,532 2,218 694 -0,270 -0,116 2,218 0,249 0,502 2,218 695 -0,234 -0,074 2,218 0,202 0,471 2,218 696 -0,197 -0,030 2,218 0,153 0,437 2,218 697 -0,159 0,013 2,218 0,105 0,402 2,218 698 -0,120 0,055 2,218 0,058 0,367 2,218 699 -0,081 0,097 2,218 0,012 0,330 2,218 700 -0,041 0,139 2,218 -0,033 0,291 2,218 701 0,000 0,180 2,218 -0,076 0,252 2,218 702 0,040 0,220 2,218 -0,119 0,211 2,218 703 0,082 0,260 2,218 -0,160 0,169 2,218 704 0,124 0,299 2,218 -0,201 0,125 2,218 705 0,166 0,338 2,218 -0,240 0,081 2,218 706 0,210 0,375 2,218 -0,277 0,036 2,218 707 0,254 0,412 2,218 -0,314 -0,010 2,218 708 0,297 0,447 2,218 -0,349 -0,056 2,218 709 0,339 0,480 2,218 -0,381 -0,101 2,218 710 0,381 0,511 2,218 -0,411 -0,144 2,218 711 0,421 0,540 2,218 -0,439 -0,187 2,218 712 0,460 0,567 2,218 -0,466 -0,229 2,218 713 0,499 0,593 2,218 -0,490 -0,269 2,218 714 0,536 0,617 2,218 -0,513 -0,308 2,218 715 0,571 0,640 2,218 -0,534 -0,346 2,218 716 0,602 0,659 2,218 -0,553 -0,380 2,218 717 0,630 0,675 2,218 -0,570 -0,412 2,218 718 0,657 0,691 2,218 -0,584 -0,440 2,218 719 0,682 0,705 2,218 -0,595 -0,467 2,218 720 0,704 0,717 2,218 -0,604 -0,491 2,218 721 0,720 0,726 2,218 -0,609 -0,510 2,218 722 0,734 0,733 2,218 -0,612 -0,525 2,218 723 0,744 0,738 2,218 -0,613 -0,537 2,218 724 0,752 0,743 2,218 -0,612 -0,546 2,218 725 0,755 0,748 2,218 -0,610 -0,551 2,218 726 0,756 0,752 2,218 -0,609 -0,553 2,218 727 0,755 0,754 2,218 -0,608 -0,554 2,218 728 0,755 0,755 2,218 -0,607 -0,555 2,218 729 -0,619 -0,579 2,343 0,713 0,786 2,343 730 -0,619 -0,579 2,343 0,713 0,786 2,343 731 -0,618 -0,579 2,343 0,712 0,787 2,343 732 -0,616 -0,579 2,343 0,711 0,789 2,343 733 -0,613 -0,579 2,343 0,707 0,791 2,343 734 -0,609 -0,576 2,343 0,700 0,791 2,343 735 -0,602 -0,571 2,343 0,692 0,788 2,343 736 -0,594 -0,562 2,343 0,681 0,783 2,343 737 -0,585 -0,550 2,343 0,666 0,777 2,343 738 -0,574 -0,534 2,343 0,648 0,770 2,343 739 -0,561 -0,512 2,343 0,624 0,760 2,343 740 -0,547 -0,487 2,343 0,596 0,747 2,343 741 -0,532 -0,460 2,343 0,567 0,734 2,343 742 -0,514 -0,430 2,343 0,536 0,720 2,343 743 -0,495 -0,396 2,343 0,502 0,704 2,343 744 -0,473 -0,360 2,343 0,463 0,684 2,343 745 -0,449 -0,322 2,343 0,422 0,663 2,343 746 -0,424 -0,283 2,343 0,380 0,640 2,343 747 -0,397 -0,242 2,343 0,336 0,615 2,343 748 -0,369 -0,200 2,343 0,292 0,588 2,343 749 -0,339 -0,158 2,343 0,246 0,560 2,343 750 -0,307 -0,114 2,343 0,199 0,530 2,343 751 -0,273 -0,069 2,343 0,151 0,497 2,343 752 -0,237 -0,023 2,343 0,102 0,462 2,343 753 -0,201 0,022 2,343 0,055 0,426 2,343 754 -0,163 0,067 2,343 0,008 0,388 2,343 755 -0,125 0,111 2,343 -0,038 0,349 2,343 756 -0,086 0,154 2,343 -0,082 0,308 2,343 757 -0,046 0,196 2,343 -0,125 0,267 2,343 758 -0,006 0,238 2,343 -0,166 0,223 2,343 759 0,035 0,280 2,343 -0,206 0,178 2,343 760 0,077 0,320 2,343 -0,245 0,133 2,343 761 0,119 0,360 2,343 -0,282 0,086 2,343 762 0,162 0,399 2,343 -0,318 0,038 2,343 763 0,206 0,437 2,343 -0,353 -0,011 2,343 764 0,249 0,473 2,343 -0,386 -0,059 2,343 765 0,292 0,507 2,343 -0,416 -0,106 2,343 766 0,333 0,539 2,343 -0,445 -0,152 2,343 767 0,374 0,569 2,343 -0,471 -0,196 2,343 768 0,414 0,597 2,343 -0,495 -0,240 2,343 769 0,452 0,623 2,343 -0,518 -0,282 2,343 770 0,490 0,647 2,343 -0,539 -0,323 2,343 771 0,526 0,670 2,343 -0,559 -0,362 2,343 772 0,557 0,689 2,343 -0,576 -0,398 2,343 773 0,586 0,706 2,343 -0,591 -0,431 2,343 774 0,613 0,721 2,343 -0,603 -0,461 2,343 775 0,638 0,735 2,343 -0,614 -0,489 2,343 776 0,660 0,747 2,343 -0,621 -0,514 2,343 777 0,677 0,756 2,343 -0,625 -0,533 2,343 778 0,691 0,764 2,343 -0,627 -0,549 2,343 779 0,701 0,769 2,343 -0,627 -0,561 2,343 780 0,709 0,773 2,343 -0,625 -0,570 2,343 781 0,713 0,778 2,343 -0,623 -0,575 2,343 782 0,714 0,782 2,343 -0,621 -0,577 2,343 783 0,714 0,784 2,343 -0,620 -0,578 2,343 784 0,713 0,785 2,343 -0,619 -0,579 2,343 785 -0,633 -0,614 2,491 0,660 0,819 2,491 786 -0,633 -0,615 2,491 0,659 0,820 2,491 787 -0,632 -0,615 2,491 0,659 0,821 2,491 788 -0,630 -0,615 2,491 0,657 0,823 2,491 789 -0,627 -0,614 2,491 0,654 0,825 2,491 790 -0,623 -0,611 2,491 0,647 0,824 2,491 791 -0,617 -0,605 2,491 0,638 0,821 2,491 792 -0,610 -0,595 2,491 0,627 0,817 2,491 793 -0,601 -0,582 2,491 0,612 0,811 2,491 794 -0,592 -0,565 2,491 0,593 0,803 2,491 795 -0,581 -0,541 2,491 0,568 0,793 2,491 796 -0,569 -0,514 2,491 0,540 0,781 2,491 797 -0,556 -0,485 2,491 0,510 0,768 2,491 798 -0,542 -0,453 2,491 0,478 0,754 2,491 799 -0,525 -0,417 2,491 0,443 0,738 2,491 800 -0,506 -0,378 2,491 0,402 0,718 2,491 801 -0,486 -0,337 2,491 0,360 0,697 2,491 802 -0,464 -0,295 2,491 0,317 0,674 2,491 803 -0,441 -0,252 2,491 0,272 0,649 2,491 804 -0,415 -0,207 2,491 0,226 0,622 2,491 805 -0,388 -0,161 2,491 0,180 0,593 2,491 806 -0,359 -0,114 2,491 0,132 0,561 2,491 807 -0,327 -0,066 2,491 0,083 0,527 2,491 808 -0,294 -0,018 2,491 0,034 0,491 2,491 809 -0,259 0,030 2,491 -0,014 0,452 2,491 810 -0,223 0,078 2,491 -0,061 0,412 2,491 811 -0,186 0,124 2,491 -0,106 0,371 2,491 812 -0,148 0,169 2,491 -0,149 0,327 2,491 813 -0,109 0,214 2,491 -0,191 0,282 2,491 814 -0,068 0,257 2,491 -0,231 0,236 2,491 815 -0,028 0,300 2,491 -0,269 0,188 2,491 816 0,014 0,343 2,491 -0,306 0,139 2,491 817 0,056 0,384 2,491 -0,342 0,089 2,491 818 0,099 0,425 2,491 -0,376 0,038 2,491 819 0,143 0,465 2,491 -0,408 -0,014 2,491 820 0,187 0,502 2,491 -0,438 -0,065 2,491 821 0,230 0,537 2,491 -0,466 -0,115 2,491 822 0,272 0,570 2,491 -0,491 -0,164 2,491 823 0,313 0,600 2,491 -0,514 -0,212 2,491 824 0,353 0,629 2,491 -0,536 -0,259 2,491 825 0,392 0,655 2,491 -0,556 -0,304 2,491 826 0,431 0,680 2,491 -0,574 -0,347 2,491 827 0,468 0,703 2,491 -0,590 -0,389 2,491 828 0,500 0,722 2,491 -0,605 -0,427 2,491 829 0,529 0,739 2,491 -0,617 -0,462 2,491 830 0,556 0,754 2,491 -0,627 -0,493 2,491 831 0,582 0,769 2,491 -0,635 -0,522 2,491 832 0,605 0,781 2,491 -0,640 -0,548 2,491 833 0,623 0,790 2,491 -0,643 -0,569 2,491 834 0,637 0,797 2,491 -0,643 -0,585 2,491 835 0,647 0,803 2,491 -0,642 -0,597 2,491 836 0,655 0,807 2,491 -0,640 -0,606 2,491 837 0,660 0,812 2,491 -0,638 -0,611 2,491 838 0,661 0,815 2,491 -0,636 -0,613 2,491 839 0,660 0,818 2,491 -0,634 -0,614 2,491 840 0,660 0,819 2,491 -0,633 -0,614 2,491

[0061] It will also be appreciated that the air vane 100 disclosed in any of the above TABLES I and II can be geometrically scaled up or down for use in other similar turbine designs. Consequently, the coordinate values ​​given in each of TABLES I and II can be scaled up or down such that the air vane profile shape remains unchanged. A scaled version of the coordinates in each of TABLES I and II would be represented by X, Y, and Z coordinate values, where the dimensionless X, Y, and Z coordinate values ​​would be converted to distance units (e.g., inches) and multiplied by or divided by a constant number.

[0062] As in Fig.4, each air deflector 100 may define a stagger angle α (alpha) measured between the chord line 110 and the axial direction A of the gas turbine 10. In particular, the stagger angle α may be measured between the chord line 110 of an air deflector 100 and the axial centerline 23 (or axis of rotation) of the gas turbine 10 at the trailing edge 108 of the air deflector 100. The stagger angle α of each air deflector 100 disclosed herein may advantageously vary along the spanwise direction 118 (or radial direction R) according to a respective stagger angle distribution. The stagger angle distribution may be a collection of stagger angles α for a given air deflector 100 at each spanwise (or radial) position along the air deflector 100.

[0063] In many embodiments, each stage S1 through S22 of the rotor blades 44 may include a unique stagger angle distribution, such that the shared use of the stages S1 through S22 of the rotor blades 44 results in a highly efficient compressor section 14. For example, each of the air vanes 100 of the rotor blades 44 in the first stage S1 may have a first stagger angle distribution, each of the air vanes 100 of the rotor blades 44 in the second stage S2 may have a second stagger angle distribution, and so on for each rotating stage (S1 through S22) of the compressor section 14.

[0064] Similarly, each stage S1 through S22 of stator vanes 50 may include a unique stagger angle distribution, such that the shared use of stages S1 through S22 of stator vanes 50 results in a highly efficient compressor section 14. For example, each of the vanes 100 of the stator vanes 50 in the first stage S1 may have a first stagger angle distribution, each of the vanes 100 of the stator vanes 50 in the second stage S2 may have a second stagger angle distribution, and so on for each stationary stage (S1 through S22) of the compressor section 14.

[0065] According to embodiments of the present disclosure, the Fig. 5 and Fig.6 each illustrates a graph of a stagger angle distribution that may be associated with one or more air vanes 100 within a specified stage (e.g., S1 to S22) of the compressor section 14. Each of the graphs may be in dimensionless units. In particular, the Y-axis illustrates a percentage along the span direction 118 (e.g., where 0% span represents the inner diameter and 100% span represents the outer diameter). For example, for a rotor blade 44, 0% span may represent the base of the air vane 100 and 100% span may represent the tip of the air vane 100. For a stator vane 50, 0% span may represent the tip of the air vane 100 and 100% span may represent the base of the air vane 100. The X-axis illustrates a relationship between the stagger angle at a specified position in the span direction and the stagger angle at mid-span (e.g.B. at about 50% range).

[0066] Each of the stagger angle distributions is plotted between 15% span and 85% span of the respective air vane 100 to which it belongs (e.g., the points for 0% to 15% span and 85% to 100% span are omitted). Each stagger angle distribution, when implemented in an air vane 100 on a rotor blade 44 and / or a stator vane 50 within the compressor section 14, advantageously increases the aerodynamic efficiency of the air vane 100 (as well as the entire compressor section 14) compared to previous designs.

[0067] In particular, Fig.5 is a graph of a stagger angle distribution plotted from 15% to 85% of the span of an air baffle 100 associated with a stator vane 50 within the seventeenth stage S17 (i.e., a seventeenth-stage stator vane). In some embodiments, all stator vanes 50 in the seventeenth stage S17 of the compressor section 14 may include an air baffle 100 having a profile defined by the X, Y, and Z coordinate values ​​of TABLE 1 and the stagger angle distribution according to Fig. 5. The Fig. 5 is plotted according to the points in TABLE III below. TABLE III Air guide vane of a stator guide vane of the seventeenth stage (%) - span Staggering / span center staggering 85,00 % 1,133 81,17 % 1,088 68,65 % 1,000 62,25 % 0,989 49,13 % 1,001 42,48 % 1,015 29,16 % 1,064 22,53 % 1,107 15,00 % 1,173

[0068] Fig.6 is a graph of a stagger angle distribution plotted from 15% to 85% span of an air baffle 100 associated with a stator vane 50 within the eighteenth stage S18 (i.e., an eighteenth-stage stator vane). In some embodiments, all of the stator vanes 50 in the eighteenth stage S18 of the compressor section 14 may include an air baffle 100 having a profile defined by the X, Y, and Z coordinate values ​​of TABLE II and the stagger distribution according to Fig. 6. The Fig. 6 is plotted according to the points in TABLE IV below. TABLE IV Air guide vane of an eighteenth-stage stator vane (%) - span Staggering / span center staggering 85,00 % 1,091 81,31 % 1,055 68,42 % 0,991 61,90 % 0,987 48,61 % 1,002 41,94 % 1,016 28,63 % 1,065 22,03 % 1,106 15,00 % 1,164

[0069] The disclosed air baffle shape optimizes and is specific to the engine conditions and specifications. It provides a unique profile to achieve 1) interaction between other stages in the compressor section 14; 2) aerodynamic efficiency; and 3) normalized aerodynamic and mechanical blade loads. The disclosed locations of points defined in each of TABLES I and II enable efficient, safe, and smooth operation of the gas turbine 10 or any other suitable turbine. As also noted, the disclosed air baffle 100 can be adapted to any scale as long as 1) interaction between other stages in the compressor section 14; 2) aerodynamic efficiency; and 3) normalized aerodynamic and mechanical blade loads are maintained in the scaled turbine.

[0070] The air baffle 100 described herein thus improves the overall efficiency of the gas turbine 10. The air baffle 100 also meets all aeromechanical and load-related requirements. For example, the air baffle 100 of the stator vane 50 has a special shape to meet the aerodynamic, mechanical, and heat transfer requirements in an efficient and cost-effective manner.

[0071] This written description uses examples to disclose the invention, including the best mode, and also to enable one skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims and may include other examples that would be apparent to one skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the language of the claims, or if they include equivalent structural elements with insubstantial changes from the language of the claims.

[0072] Further aspects of the invention are provided by the subject matter of the following paragraphs: A stator vane comprising: an air vane having an air vane shape, the air vane shape having a nominal profile substantially according to the Cartesian coordinate values ​​of X, Y, and Z listed in one of TABLE I and TABLE II, the Cartesian coordinate values ​​of X, Y, and Z being defined relative to a point data origin at a base of the air vane, the Cartesian coordinate values ​​of X, Y, and Z being dimensionless values ​​convertible into dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a scaling factor of the air vane in the unit of distance;and wherein the X and Y values ​​are connected by smooth, continuous arcs, thus defining airfoil profile sections at each Z value, the airfoil profile sections being smoothly connected to one another at the Z values, thus forming a complete airfoil shape.;

[0073] The stator vane according to any one of the preceding paragraphs, wherein the air guide vane includes a stagger angle distribution, each stagger angle in the stagger angle distribution being measured between a chord line of the air guide vane and an axis of rotation of the air guide vane; wherein, when the air guide vane is defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE I, the stagger angle distribution is defined according to TABLE III; and wherein, when the air guide vane is defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE II, the stagger angle distribution is defined according to TABLE IV.

[0074] The stator vane according to any one of the preceding paragraphs, wherein the stator vane forms part of a middle stage of a compressor section.

[0075] The stator vane of any preceding paragraph, wherein the stator vane is defined by TABLE I and is a seventeenth stage compressor stator vane.

[0076] The stator vane of any preceding paragraph, wherein the stator vane is defined by TABLE II and is an eighteenth stage compressor stator vane.

[0077] The stator vane according to any one of the preceding paragraphs, wherein the air deflector shape lies in an envelope within + / -5% of a chord length in a direction normal to any position of the air deflector surface.

[0078] The stator vane of any preceding paragraph, wherein the scale factor is between about 0.01 inches and about 10 inches.

[0079] The stator vane of any preceding paragraph, wherein the X, Y, and Z values ​​are scalable depending on the same constant or number to provide a scaled-up or scaled-down air deflector.

[0080] A stator vane comprising: an air guide vane having a nominal suction side profile substantially according to the suction side Cartesian coordinate values ​​of X, Y, and Z listed in one of TABLE I or TABLE II, wherein the Cartesian coordinate values ​​of X, Y, and Z are defined relative to a point data origin at a base of the air guide vane, wherein the Cartesian coordinate values ​​of X, Y, and Z are dimensionless values ​​convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a scaling factor of the air guide vane in the unit of distance; and wherein the X and Y values ​​are connected by smooth, continuous arcs to define suction side profile sections at each Z value, the suction side profile sections being smoothly connected to one another at the Z values ​​to form a complete suction side shape of the air guide vane.

[0081] The stator vane according to any one of the preceding paragraphs, wherein the air guide vane includes a stagger angle distribution, each stagger angle in the stagger angle distribution being measured between a chord line of the air guide vane and an axis of rotation of the air guide vane; wherein, when the air guide vane has the nominal suction side profile defined by the Cartesian coordinate values ​​of X, Y and Z listed in TABLE I, the stagger angle distribution is defined according to TABLE III; and wherein, when the air guide vane has the nominal suction side profile defined by the Cartesian coordinate values ​​of X, Y and Z listed in TABLE II, the stagger angle distribution is defined according to TABLE IV.

[0082] The stator vane according to any one of the preceding paragraphs, wherein the stator vane forms part of a middle stage of a compressor section.

[0083] The stator vane of any preceding paragraph, wherein the stator vane is defined by TABLE I and is a seventeenth stage compressor stator vane.

[0084] The stator vane of any preceding paragraph, wherein the stator vane is defined by TABLE II and is an eighteenth stage compressor stator vane.

[0085] The stator vane according to any one of the preceding paragraphs, wherein the nominal suction side profile lies in an envelope within + / -5% of a chord length in a direction normal to any position of the air deflector surface.

[0086] The stator vane of any preceding paragraph, wherein the scale factor is between about 0.01 inches and about 10 inches.

[0087] The stator vane of any preceding paragraph, wherein the X, Y, and Z values ​​are scalable depending on the same constant or number to provide a scaled-up or scaled-down air deflector.

[0088] A turbomachine comprising: a compressor section; a turbine section downstream of the compressor section; a combustion section downstream of the compressor section and upstream of the turbine section;and a stator vane disposed in the compressor section, the stator vane comprising: an air baffle having an air baffle shape, the air baffle shape having a nominal profile substantially according to the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE I or TABLE II, the Cartesian coordinate values ​​of X, Y, and Z being defined relative to a point data origin at a base of the air baffle, the Cartesian coordinate values ​​of X, Y, and Z being dimensionless values ​​convertible into dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a height of the air baffle in the unit of distance;and wherein the X and Y values ​​are connected by smooth, continuous arcs, thus defining airfoil profile sections at each Z value, the airfoil profile sections being smoothly connected to one another at the Z values, thus forming a complete airfoil shape.;

[0089] The turbomachine according to any one of the preceding paragraphs, wherein the air deflector includes a stagger angle distribution, each stagger angle in the stagger angle distribution being measured between a chord line of the air deflector and an axis of rotation of the air deflector; wherein, when the air deflector has the nominal suction side profile defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE I, the stagger angle distribution is defined according to TABLE III; and wherein, when the air deflector has the nominal suction side profile defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE II, the stagger angle distribution is defined according to TABLE IV.

Claims

A stator vane comprising: an air vane having an air vane shape, the air vane shape having a nominal profile substantially according to the Cartesian coordinate values ​​of X, Y, and Z listed in one of Table I or Table II, the Cartesian coordinate values ​​of X, Y, and Z being defined relative to a point data origin at a base of the air vane, the Cartesian coordinate values ​​of X, Y, and Z being dimensionless values ​​convertible into dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a scaling factor of the air vane in the unit of distance; and the X and Y values ​​being connected by smooth, continuous arcs, thus defining air vane profile sections at each Z value, the air vane profile sections being smoothly connected to one another at the Z values, thus forming a complete air vane shape. The stator vane of claim 1, wherein the air guide vane includes a stagger angle distribution, each stagger angle in the stagger angle distribution being measured between a chord line of the air guide vane and an axis of rotation of the air guide vane; wherein, when the air guide vane is defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE I, the stagger angle distribution is defined according to TABLE III; and wherein, when the air guide vane is defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE II, the stagger angle distribution is defined according to TABLE IV. Stator vane according to claim 1, wherein the stator vane forms part of a middle stage of a compressor section. The stator vane of claim 3, wherein the stator vane is defined by TABLE I and is a seventeenth stage compressor stator vane. The stator vane of claim 3, wherein the stator vane is defined by TABLE II and is an eighteenth stage compressor stator vane. Stator vane according to claim 1, wherein the air baffle shape lies in an envelope within + / -5% of a chord length in a direction normal to any position of the air baffle surface. The stator vane of claim 1, wherein the scaling factor is between about 0.01 inches and about 10 inches. The stator vane of claim 1, wherein the X, Y, and Z values ​​are scalable depending on the same constant or number to provide a scaled-up or scaled-down air baffle. A stator vane comprising:an air baffle having a nominal suction side profile substantially according to the suction side Cartesian coordinate values ​​of X, Y, and Z listed in one of TABLE I or TABLE II, wherein the Cartesian coordinate values ​​of X, Y, and Z are defined relative to a point data origin at a base of the air baffle, wherein the Cartesian coordinate values ​​of X, Y, and Z are dimensionless values ​​convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a scaling factor of the air baffle in the unit of distance; and wherein the X and Y values ​​are connected by smooth, continuous arcs to define suction side profile sections at each Z value, the suction side profile sections being smoothly connected to one another at the Z values ​​to form a complete suction side shape of the air baffle. The stator vane of claim 8, wherein the air guide vane includes a stagger angle distribution, each stagger angle in the stagger angle distribution being measured between a chord line of the air guide vane and an axis of rotation of the air guide vane; wherein, when the air guide vane has the nominal suction side profile defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE I, the stagger angle distribution is defined according to TABLE III; and wherein, when the air guide vane has the nominal suction side profile defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE II, the stagger angle distribution is defined according to TABLE IV. Stator vane according to claim 9, wherein the stator vane forms part of a middle stage of a compressor section. The stator vane of claim 11, wherein the stator vane is defined by TABLE I and is a seventeenth stage compressor stator vane. The stator vane of claim 11, wherein the stator vane is defined by TABLE II and is an eighteenth stage compressor stator vane. A stator vane according to claim 9, wherein the nominal suction side profile lies in an envelope within + / -5% of a chord length in a direction normal to any position of the air deflector surface. The stator vane of claim 9, wherein the scaling factor is between about 0.01 inches and about 10 inches. The stator vane of claim 9, wherein the X, Y, and Z values ​​are scalable depending on the same constant or number to provide a scaled-up or scaled-down air baffle. A turbomachine comprising:a compressor section;a turbine section downstream of the compressor section;a combustion section downstream of the compressor section and upstream of the turbine section; anda stator vane disposed in the compressor section, the stator vane comprising:an air baffle having an air baffle shape, the air baffle shape having 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 a base of the air baffle, the Cartesian coordinate values ​​of X, Y, and Z being dimensionless values ​​convertible into dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values ​​of X, Y, and Z by a height of the air baffle in the unit of distance;and wherein the X and Y values ​​are connected by smooth, continuous arcs, thus defining airfoil profile sections at each Z value, the airfoil profile sections being smoothly connected to one another at the Z values, thus forming a complete airfoil shape.; The turbomachine of claim 17, wherein the air baffle includes a stagger angle distribution according to TABLE II, wherein each stagger angle in the stagger angle distribution is measured between a chord line of the air baffle and an axis of rotation of the air baffle; wherein, when the air baffle has the nominal suction side profile defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE I, the stagger angle distribution is defined according to TABLE III; and wherein, when the air baffle has the nominal suction side profile defined by the Cartesian coordinate values ​​of X, Y, and Z listed in TABLE II, the stagger angle distribution is defined according to TABLE IV.

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