Pneumatic variable turbine nozzle

Abstract

A pneumatic variable nozzle vane (200) capable of performing the same or similar functions as a mechanical variable nozzle vane is disclosed. Within its core, each pneumatically variable nozzle vane may include one or more cavities (200) in fluid communication with one or more outlets (230) to inject gas from the nozzle vane into a flow path of working fluid through the nozzle. Each cavity may be shaped such that the internal pressure gradient matches the external pressure gradient of the nozzle vane. The gas may be injected as a curtain, substantially perpendicular to the flow path through the nozzle, to manipulate the flow of the working fluid through the nozzle in a manner similar to a mechanically variable nozzle vane. In an embodiment, each nozzle vane may have two cavities that provide outlets on a pressure side and a suction side of the nozzle vane.

Description

Technical Field

[0001] The embodiments described herein relate generally to nozzles for turbomachines, and more particularly, to aerodynamically variable nozzles in turbomachines. Background Art

[0002] In a gas turbine engine, the pressure ratio of the compressor and the turbine can be adjusted relative to each other according to the expected operation of the gas turbine engine. Traditionally, the pressure ratio of the turbine can be adjusted using mechanically variable nozzle vanes within the turbine. In particular, these mechanically variable nozzle vanes rotate around a radial axis within a certain angle range.

[0003] It would be beneficial to be able to use gas (such as bleed air from a compressor) to achieve the same function as a mechanically variable nozzle vane. In particular, the injection of gas from the nozzle vane can be used to affect the airflow through the nozzle in the same way that mechanically rotating nozzle vanes affect the airflow through the nozzle. In other words, the inventors have determined that a pneumatically variable nozzle can perform the same function as a mechanically variable nozzle.

[0004] There are a variety of methods for injecting gas from nozzle vanes in different situations. For example, U.S. Patent Publication No. 2017 / 0051680 discloses a nozzle that uses openings on the pressure side of each nozzle vane to introduce bleed air into a turbine. U.S. Patent No. 11,149,549 describes a vane in a steam turbine that injects steam from openings on the pressure side and the suction side. U.S. Patent No. 6,530,744 discloses a nozzle vane with openings for delivering cooling air into the flow path of the engine.

[0005] The present invention is directed to overcoming one or more problems discovered by the inventors. For example, conventional nozzle vanes may produce non-constant radial pressure gradients under full-load and part-load engine operating conditions, internal geometry for core and hole placement in nozzle vanes is limited, straight circular holes through the surface of the nozzle vanes may cause structural problems when placed too close to each other, and injecting gas from the nozzle vanes at angles that are not perpendicular to the direction of flow through the nozzle may not be as effective in manipulating gas flow through the nozzle. Summary of the invention

[0006] In an embodiment, a nozzle vane includes: an inlet through a first radial end of the nozzle vane; a cavity located in a core of the nozzle vane, the cavity extending from the inlet toward a second radial end of the nozzle vane, wherein a cross-sectional area of ​​the cavity decreases from the first radial end to the second radial end along a radial axis of the nozzle vane; and an outlet through a side surface of the nozzle vane, the outlet being in fluid communication with the cavity.

[0007] In an embodiment, a nozzle vane includes: a front inlet passing through a first radial end of the nozzle vane; a front cavity located in a core of the nozzle vane, the front cavity extending from the front inlet toward a second radial end of the nozzle vane, wherein a cross-sectional area of ​​the front cavity decreases along a radial axis from the first radial end to the second radial end of the nozzle vane; a front outlet passing through a suction side surface of the nozzle vane; a front passage connecting the front cavity to the front outlet; a rear inlet passing through the first radial end of the nozzle vane; a rear cavity located in the core of the nozzle vane, the rear cavity extending from the rear inlet toward the second radial end, wherein a cross-sectional area of ​​the rear cavity decreases along the radial axis from the first radial end to the second radial end; a rear outlet passing through a pressure side surface of the nozzle vane; and a rear passage connecting the rear cavity to the rear outlet.

[0008] In an embodiment, a gas turbine engine includes: a compressor; a combustor downstream of the compressor; and a turbine downstream of the combustor, wherein the turbine includes a nozzle, the nozzle including a plurality of nozzle vanes arranged annularly around a longitudinal axis of the gas turbine engine, and wherein each of the plurality of nozzle vanes includes an inlet through a first radial end of the nozzle vane, a cavity located within a core of the nozzle vane, the cavity extending from the inlet toward a second radial end of the nozzle vane, wherein a cross-sectional area of ​​the cavity decreases from the first radial end to the second radial end along the radial axis of the nozzle vane; and an outlet through a side surface of the nozzle vane, the outlet being fluidically connected to the cavity. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Details of embodiments of the present invention, both as to its structure and operation, may be gleaned in part by studying the accompanying drawings, in which like reference numerals represent like parts, and in which:

[0010] Figure 1 shows a schematic diagram of a gas turbine engine according to an embodiment;

[0011] FIG. 2A to FIG. 2C illustrates the general operation of an embodiment of an aerodynamically variable nozzle vane according to an example, using a simplified rectangular vane elevation cross-sectional view;

[0012] Figure 3 shows the profile of two adjacent nozzle vanes viewed downward along a radial axis according to an embodiment;

[0013] Figures 4 to 6 shows an aerodynamic variable nozzle vane according to a first embodiment; and

[0014] Figures 7 to 10 An aerodynamic variable nozzle vane according to a second embodiment is shown. DETAILED DESCRIPTION

[0015] The detailed description set forth below in conjunction with the accompanying drawings is intended as a description of various embodiments, rather than being intended to represent the only embodiment in which the present invention can be practiced. The detailed description includes specific details for providing a thorough understanding of the embodiments. However, it is apparent to those skilled in the art that embodiments of the present invention may be practiced without these specific details. In some cases, known structures and components are shown in simplified form for brevity of description.

[0016] For clarity and ease of explanation, some surfaces and details may be omitted in this specification and the accompanying drawings. In addition, unless otherwise specified, the "upstream" and "downstream" or "forward" and "rearward" mentioned herein are relative to the flow direction of the main gas (e.g., air) used in the combustion process. It should be understood that "upstream", "forward" and "front" refer to a position closer to the main gas source or a direction toward the main gas source, while "downstream", "rearward" and "rear" refer to a position farther away from the main gas source or a direction away from the main gas source. Therefore, the trailing edge or end of a component (e.g., a turbine blade) is located downstream of the leading edge or end of the same component. In addition, it should be understood that, as used herein, the terms "side", "top", "bottom", "front" and "rear" are used for ease of understanding to convey the relative positions of various components relative to each other, and do not imply any particular orientation of those components in absolute terms (e.g., relative to the external environment or the ground).

[0017] It should also be understood that the various components shown herein are not necessarily drawn to scale. In other words, the features disclosed in the various embodiments may be implemented using relative dimensions within and between components that are different from those shown in the drawings.

[0018] Figure 1 A schematic diagram of a gas turbine engine 100 according to an embodiment is shown. The gas turbine engine 100 includes a shaft 102 having a central longitudinal axis L. Various other components of the gas turbine engine 100 are concentric with the longitudinal axis L and may be annular relative to the longitudinal axis L. A radial axis may refer to any axis or direction radiating outward from the longitudinal axis L at an angle substantially orthogonal to the longitudinal axis L, such as Figure 1 Thus, the term "radially outward" shall be understood as away from or away from the longitudinal axis L, and the term "radially inward" shall be understood as closer to or toward the longitudinal axis L. As used herein, the term "radial" shall refer to any axis or direction substantially perpendicular to the longitudinal axis L, and the term "axial" shall refer to any axis or direction substantially parallel to the longitudinal axis L.

[0019] In an embodiment, the gas turbine engine 100 includes an inlet 110, a compressor 120, a combustor 130, a turbine 140, and an exhaust outlet 150 from the upstream end to the downstream end. In addition, the downstream end of the gas turbine engine 100 may include a power output coupling 104. One or more (possibly including all) of these components of the gas turbine engine 100 may be made of stainless steel and / or a durable high-temperature material called a "superalloy". Superalloys are alloys that exhibit excellent mechanical strength and creep resistance, good surface stability, and corrosion resistance and oxidation resistance at high temperatures. Examples of superalloys include, but are not limited to, Hastelloy, Inconel, Waspaloy, Rene nickel-based high temperature corrosion resistant (Rene) alloys, Haynes alloys, Incoloy alloys, MP98T, TMS alloys, and CMSX single crystal alloys.

[0020] The inlet 110 may deliver a working fluid F (e.g., a primary gas, such as air) into an annular flow path 112 about a longitudinal axis L. The working fluid F flows through the inlet 110 into the compressor 120. Although the working fluid F is shown as flowing into the inlet 110 from a particular direction and at an angle substantially orthogonal to the longitudinal axis L, it should be understood that the inlet 110 may be configured to receive the working fluid F from any direction and at any angle suitable for a particular application of the gas turbine engine 100. Although the working fluid F will be primarily described herein as air, it should be understood that the working fluid F may include other fluids, including other gases.

[0021] The compressor 120 may include a series of compressor rotor assemblies 122 and stator assemblies 124. Each compressor rotor assembly 122 may include a rotor disk, the circumference of which is filled with a plurality of rotor blades. The rotor blades in the rotor disk are separated from the rotor blades in the adjacent disk along the axial axis by the compressor stator assembly 124. The compressor 120 compresses the working fluid F through a series of stages corresponding to each compressor rotor assembly 122. The compressed working fluid F then flows from the compressor 120 into the combustor 130.

[0022] The combustor 130 may include a combustor casing 132 that houses one or more, and typically a plurality of, fuel injectors 134. In embodiments having a plurality of fuel injectors 134, the fuel injectors 134 may be arranged circumferentially within the combustor casing 132 at equally spaced intervals about the longitudinal axis L. The combustor casing 132 diffuses the working fluid F, and the fuel injectors 134 inject fuel into the working fluid F. The injected fuel is ignited to produce a combustion reaction in one or more combustion chambers 136. The products of the combustion reaction drive the turbine 140.

[0023] The turbine 140 may include one or more turbine rotor assemblies 142 and a stator assembly 144. The turbine stator assembly 144 may also be referred to herein as a "nozzle" and includes a plurality of radially extending nozzle blades arranged annularly around the longitudinal axis L. Each turbine rotor assembly 142 may correspond to one of a plurality of or a series of stages. The turbine 140 extracts energy from the burning fuel-gas mixture as it passes through each stage. The energy extracted by the turbine 140 may be transferred (e.g., to an external system) via the power output coupling 104, and transferred to the compressor 120 via the shaft 102.

[0024] The exhaust gas E from the turbine 140 may flow into the exhaust outlet 150. The exhaust outlet 150 may include an exhaust diffuser 152 that diffuses the exhaust gas E and an exhaust collector 154 that collects, redirects, and outputs the exhaust gas E. It should be understood that the exhaust gas E output by the exhaust collector 154 may be further processed, for example, to reduce harmful emissions, recover heat, etc. In addition, although the exhaust gas E is shown as flowing out of the exhaust outlet 150 from a particular direction and at an angle substantially orthogonal to the longitudinal axis L, it should be understood that the exhaust outlet 150 may be configured to output the exhaust gas E in any direction and at any angle suitable for a particular application of the gas turbine engine 100.

[0025] FIG. 2A to FIG. 2C The general operation of an embodiment of an aerodynamic variable nozzle vane according to three examples is shown, using a front cross-sectional view of a simplified rectangular vane. Each aerodynamic variable nozzle vane 200 includes a cavity 220 extending to its core. Gas (e.g., air) is injected into the cavity 220 through an inlet 210. The gas may be bleed air supplied to the inlet 210 of each nozzle vane 200 from a stage or output of the compressor 120 via a bleed circuit. The gas is ejected from the cavity 220 of each nozzle vane 200 through one or more openings 230. Each opening 230 may be formed through the side surface of the nozzle vane 200, as described in more detail elsewhere herein, so as to be ejected into the path of the working fluid F flowing through the adjacent nozzle vane 200 (e.g., from the combustor 130).

[0026] The cavity 220 may be defined by a tapered surface 240 such that the cross-sectional area of ​​the cavity 220 cut in a plane perpendicular to the radial axis decreases from one end to the other along the radial axis. As shown, the cross-sectional area of ​​each cavity 220 decreases from the open end of the cavity 220 where the inlet 210 is located to the relatively closed end of the cavity 220.

[0027] The tapered surface 240 is shown in only a few linear-based examples to illustrate the general operation of the nozzle vane 200. In practice, the tapered surface 240 can be formed into more complex shapes, with curvatures and other geometric contours, whose cross-sectional area decreases from the open end to the closed end of the cavity 220. In particular, the tapered surface 240 can be designed to produce a desired internal pressure distribution within the cavity 220. For example, the nozzle vane 200A includes a fully proportional tapered surface 240 to produce a uniform internal pressure gradient 250A from one end to the opposite end across the cavity 220. Therefore, the static pressure at each opening 230 will be the same. As another example, the nozzle vane 200B includes a first tapered surface 240A that changes (e.g., accelerates) the airflow through a subset of the openings 230 before transitioning to the second tapered surface 240B. This creates an internal pressure gradient 250B that has a highest static pressure at the openings 230 closest to the inlet 210 and decreases to its lowest static pressure at the openings 230 farthest from the inlet 210. As another example, the nozzle vane 200C includes a first tapered surface 240A that changes (e.g., slows down) the airflow through a first subset of the openings 230 before transitioning to the second tapered surface 240B. This creates an internal pressure gradient 250C that has a lowest static pressure at the openings 230 closest to the inlet 210 and increases to its highest static pressure at the openings 230 farthest from the inlet 210. In an embodiment, the tapered surface 240 may be designed to create an internal pressure gradient that matches the external pressure gradient along the radial span of the nozzle vane 200 so that gas is ejected from all openings 230 at a constant pressure. It should be understood that the pressure gradients at each of the first and second tapered surfaces 240A and 240B may be configured to match the external pressure gradient along the radial span of the nozzle vane 200 so that gas is ejected from all openings 230 at a constant pressure. Figure 2A , Figure 2B and Figure 2C The internal pressure gradients 250A, 250B, and 250C shown in are not physical features of the nozzle vane 200 , but are overlays to illustrate the basic internal pressure gradients 250 produced by the corresponding tapered surfaces 240 .

[0028] Figure 3The profile of two adjacent nozzle vanes 200 viewed downward along a radial axis according to an embodiment is shown. Each nozzle vane 200 may include a leading edge 310 and a trailing edge 320. In addition, each nozzle vane 200 may include a pressure side surface 330 and a suction side surface 340. Points P1, P2, P3, P4, P5, P6, P7, and P8 represent various locations where gas may be ejected from the nozzle vane 200 through the pressure side surface 330, and points S1, S2, S3, S4, S5, S6, S7, and S8 represent various locations where gas may be ejected from the nozzle vane 200 through the suction side surface 340. It should be understood that these points represent only a sample of locations that may be used as reference points herein, and that gas may be ejected from the nozzle vane 200 at any point along the pressure side surface 330 and / or the suction side surface 340. The following table provides the locations of points in the form of percentages of the length of the curve from the leading edge 310 to the trailing edge 320 along their respective surfaces. It should be understood that these points are given as example references only, and although described as having values ​​to two decimal places, such precise values ​​are not a requirement for any embodiment, and less precise values ​​are contemplated.

[0029]

[0030] The turbine stator assembly 144 may include a plurality of nozzle vanes 200 arranged circumferentially along a radial axis about the longitudinal axis L. It should be appreciated that each nozzle vane 200 may be secured to an inner annular structure on a radially inner end and an outer annular structure on a radially outer end so as to be retained within the flow path of a working fluid F passing through the turbine 140. Thus, the working fluid F (e.g., exiting the combustor 130) will flow between each pair of adjacent nozzle vanes 200.

[0031] like FIG. 2A to FIG. 2C As shown, each nozzle vane 200 may have an inlet end in which one or more inlets 210 are formed and a closed end opposite the inlet end. Depending on the specific design of the turbine 140, the bleed circuit within the gas turbine engine 100, etc., the nozzle vane 200 may be oriented so that the inlet end is the radially inner end (e.g., fixed to an inner annular structure), or may be oriented so that the inlet end is the radially outer end (e.g., fixed to an outer annular structure). Therefore, it should be understood that although the disclosed embodiments may be illustrated as the inlet end of the nozzle vane 200 being the radially inner end, the disclosed embodiments may be equally easily implemented with the inlet end of the nozzle vane 200 being the radially outer end.

[0032] In either case, each inlet 210 may be connected to a gas circuit (e.g., a bleed circuit) within the annular structure to which it is fixed, such that gas is supplied from the gas circuit through each inlet 210 into the corresponding cavity 220. Although not shown, the gas turbine engine 100 may include an aerodynamic variable turbine gas delivery system, including pipes and / or conduits forming a flow path of the gas circuit (e.g., a bleed circuit), one or more control valves, one or more manifolds, etc. The aerodynamic variable turbine gas delivery system may also include one or more controllers capable of controlling other components of the aerodynamic variable turbine gas delivery system, such as control valves, to deliver gas (e.g., output from the compressor 120 or one or more stages) to the nozzle vanes 200 of the nozzle as needed and according to one or more controlled parameters, such as volume, pressure, temperature, gas mixture, etc., to achieve a desired flow rate of the mainstream of the working fluid F through the nozzle.

[0033] Figures 4 to 6 The aerodynamic variable nozzle vane 200 according to the first embodiment is shown. Specifically, Figure 4 A view of the inlet end of the nozzle vane 200 is shown along the radial axis of the nozzle vane 200, Figure 5 shows a perspective view of the pressure side surface 330 of the nozzle vane 200 according to the first embodiment, Figure 6 A perspective view of the suction side surface 340 of the nozzle vane 200 is shown.

[0034] like Figure 4 As shown, the inlet end of the nozzle vane 200 includes a front inlet 411 and a rear inlet 421. The front inlet 411 provides a flow path into the front cavity 410, and the rear inlet 421 provides a flow path into the rear cavity 420. The front cavity 410 is closer to the leading edge 310 than the rear cavity 420, and the rear cavity 420 is closer to the trailing edge 320 than the front cavity 410. It should be understood that conceptually, the front inlet 411 and the rear inlet 421 each correspond to FIG. 2A to FIG. 2C In addition, conceptually, the front cavity 410 and the rear cavity 420 each correspond to FIG. 2A to FIG. 2C The cavity 220 is formed in the cavity.

[0035] The forward cavity 410 is in fluid communication with a passage 412 that provides a flow path to an outlet 414. The outlet 414 provides a flow path from the passage 412 to the exterior of the nozzle vane 200 through the suction side surface 340. As shown, the passage 412 may be substantially narrower than the forward cavity 410 and may narrow from the forward cavity 410 to the outlet 414. However, in alternative embodiments, the passage 412 may have a width that is similar, the same, or greater than the width of the forward cavity 410 and / or may have a constant width or widen from the forward cavity to the outlet 414. It should be understood that, conceptually, the outlet 414 corresponds to FIG. 2A to FIG. 2C The opening 230 in the embodiment of the present invention may be formed as one elongated opening rather than a plurality of separate openings.

[0036] The passage 412 may include one or more ribs 416 extending across the passage 412 to provide structural support to the nozzle vane 200. Figure 5 and Figure 6 As shown, a plurality of ribs 416 may be formed at equal intervals along a radial axis passing through the channel 412. The ribs 416 may divide a portion of the channel 412 into a plurality of separate channels. However, another portion of the channel 412, for example, between the rib-divided portion of the channel 412 and the outlet 414, may remain undivided.

[0037] In the illustrated embodiment, the channel 412 extends from the rear of the front cavity 410 and then bends so that the outlet 414 extends through the suction side surface 340 at a substantially perpendicular angle (e.g., + / -5° or + / -10°) to the suction side surface 340 at the location of the outlet 414. In other words, the gas will be ejected from the outlet 414 at an angle substantially perpendicular to the working fluid F flowing through the suction side surface 340. Figure 6 As shown, the outlet 414 may include a single continuous elongated radial opening through the suction side surface 340. The radial length of the outlet 414 may match (i.e., be the same as or similar to) the radial length from one radial end of the front cavity 410 to the opposite radial end of the front cavity 410. Thus, the air curtain will be ejected from the outlet 414 along the entire radial span of the front cavity 410. In an embodiment, the outlet 414 is positioned on the suction side surface 340 at a point between points S4 and S6, such as at point S4 (i.e., 39.55% curve, or -18% from the throat defined by the line passing through the closest distance between a pair of adjacent nozzle vanes 200, which will be defined by points S7 and P8 in the example shown), point S5 (i.e., 45.64% curve, or -12% from the throat) or point S6 (i.e., 51.78% curve, or -6% from the throat).

[0038] In an embodiment, gas flows into the front cavity 410 through the front inlet 411, flows from the front cavity 410 into a plurality of rib-separated channels in a first portion of the channel 412, converges in a second portion of the channel 412, and is ejected from a single continuous elongated radial outlet 414 as a curtain of gas that is substantially perpendicular to the suction side surface 340. However, it should be understood that this is an example embodiment and other embodiments are possible. For example, in alternative embodiments, the ribs 416 may be omitted, the ribs 416 may extend the entire length of the channel 412, the ribs 416 may extend along different portions of the channel 412, the outlet 414 may be formed as a plurality of separate openings, the channel 412 and / or the outlet 414 may be configured to eject gas at a non-perpendicular angle relative to the suction side surface 340 (e.g., at a non-perpendicular downstream angle), and / or the like.

[0039] As shown, the front cavity 410 may include a tapered surface 418. It should be understood that, conceptually, the tapered surface 418 corresponds to FIG. 2A to FIG. 2C 4. In the illustrated embodiment, the tapered surface 418 initially has a less steep slope relative to the radial axis in order to change (e.g., accelerate) the flow through the front cavity 410 before transitioning to a steeper slope relative to the radial axis. Thus, the tapered surface 418 will produce an internal pressure gradient similar to the internal pressure gradient 250B.

[0040] The rear cavity 420 is in fluid communication with a passage 422 that provides a flow path to an outlet 424. The outlet 424 provides a flow path from the passage 422 through the pressure side surface 330 to the exterior of the nozzle vane 200. As shown, the passage 422 may extend from the cavity 420 toward the trailing edge 320 and then bend or turn toward the pressure side surface 330 to connect to the outlet 424. On the pressure side surface 330, the effectiveness of gas injection tends to increase as the distance from the trailing edge 320 decreases. Therefore, in an embodiment, the outlet 424 is located on the pressure side surface 330 between points P7 and P8. It should be understood that, conceptually, the outlet 424 corresponds to FIG. 2A to FIG. 2C The opening 230 in the embodiment of the present invention may be formed as one elongated opening rather than a plurality of separate openings.

[0041] The passage 422 may include one or more ribs 426 extending across the passage 422 to provide structural support to the nozzle vane 200. Figure 5 and Figure 6 As shown, a plurality of ribs 426 may be formed at equal intervals along a radial axis passing through the channel 422. These ribs 426 may divide a portion of the channel 422 into a plurality of separate channels. However, another portion of the channel 422, for example, between the rib-divided portion of the channel 422 and the outlet 424, may remain undivided.

[0042] In the illustrated embodiment, the passage 422 extends from the rear of the rear cavity 420 and then bends so that the outlet 424 extends through the pressure side surface 330 at a substantially perpendicular angle (e.g., + / -5° or + / -10°) to the pressure side surface 330 at the location of the outlet 424. In other words, the gas will be ejected from the outlet 424 at an angle substantially perpendicular to the working fluid F flowing through the pressure side surface 330. Figure 5 As shown, the outlet 424 may include a single, continuous, elongated radial opening through the pressure side surface 330. The radial length of the outlet 424 may match (i.e., be the same as or similar to) the radial length from one radial end of the rear cavity 420 to the opposite radial end of the rear cavity 420. Thus, the air curtain will be ejected from the outlet 424 along the entire radial span of the rear cavity 420. In an embodiment, the outlet 424 is positioned on the pressure side surface 330 between points P7 and P8, including, for example, point P7 (i.e., 81.24% bend), point P7.25 (i.e., 85.84% bend), or point P7.5 (i.e., 89.65% bend). It is generally beneficial to position the outlet 424 as close to the trailing edge 320 (approximately corresponding to point P8) as possible within given manufacturing constraints.

[0043] In an embodiment, gas flows into the rear cavity 420 through the rear inlet 421, flows from the rear cavity 420 into a plurality of rib-separated channels in a first portion of the channel 422, converges in a second portion of the channel 422, and is ejected from a single continuous elongated radial outlet 424 as a curtain of gas that is substantially perpendicular to the pressure side surface 330. However, it should be understood that this is an example embodiment and other embodiments are possible. For example, in alternative embodiments, the ribs 426 may be omitted, the ribs 426 may extend the entire length of the channel 422, the ribs 426 may extend along different portions of the channel 422, the outlet 424 may be formed as a plurality of separate openings, the channel 422 and / or the outlet 424 may be configured to eject gas at a non-perpendicular angle relative to the pressure side surface 330 (e.g., at a non-perpendicular downstream angle), and / or the like.

[0044] As shown, the cavity 420 may include a tapered surface 428. It should be understood that, conceptually, the tapered surface 428 corresponds to FIG. 2A to FIG. 2C In the embodiment shown, the tapered surface 428 has a substantially uniform slope from one end to the other. Therefore, the tapered surface 428 will generate an internal pressure gradient similar to the internal pressure gradient 250A.

[0045] Figures 7 to 10 An aerodynamic variable nozzle vane 200 according to a second embodiment is shown. Specifically, Figure 7 A view of the inlet end of the nozzle vane 200 is shown along the radial axis of the nozzle vane 200, Figure 8 shows a perspective view of the pressure side surface 330 of the nozzle vane 200, Fig. 9 A perspective view of the suction side surface 340 of the nozzle vane 200 is shown, and Fig.10 A perspective view of a cross-sectional portion of the trailing edge 320 of the nozzle vane 200 according to the second embodiment is shown. The second embodiment differs from the first embodiment in the configuration of the passage and outlet of the rear cavity 420. In all other respects, the second embodiment may be similar or identical to the first embodiment. Therefore, the description of the front inlet 412, the front cavity 410, the passage 412, the outlet 414, the rib 416 and the tapered surface 418 and the rear inlet 421, the rear cavity 420 and the tapered surface 428 of the first embodiment also applies to those same components in the second embodiment.

[0046] like Figure 7 As shown, the rear cavity 420 is in fluid communication with a passage 722, which provides a flow path to an outlet 724. The outlet 724 provides a flow path from the passage 722 to the outside of the nozzle vane 200 through the pressure side surface 330. The passage 722 may extend from the rear cavity 420 toward and as close to the trailing edge 320 as possible to connect to the outlet 724. For example, the tail end of the outlet 724 may correspond to point P8. It is worth noting that the outlet 724 in the second embodiment may be wider than the outlet 424 in the first embodiment so that the tail end of the outlet 724 can be positioned closer to the trailing edge 320. In essence, the passage 722 is formed as a linear passage, or a slightly curved passage that follows the curvature of the pressure side surface 330 and / or the suction side surface 340, extending from the rear of the rear cavity 420 toward the trailing edge 320, wherein a portion of the pressure side surface 330 near the trailing edge 320 is removed to form the outlet 724, and the outlet 724 exposes the tail end of the passage 722.

[0047] The passage 722 may include one or more ribs 726 extending across the passage 722 to provide structural support to the nozzle vane 200. Figure 8 and Fig. 9 As shown, a plurality of ribs 726 may be formed at equal intervals along a radial axis passing through the channel 722. These ribs 726 may divide at least a portion of the channel 722 into a plurality of separate channels. In the illustrated embodiment, the ribs 726 divide the entire channel 722 into a plurality of separate channels. However, in alternative embodiments, the ribs 726 may divide only a portion (e.g., the front, middle, or rear) of the channel 722 into a plurality of separate channels.

[0048] In the illustrated embodiment, the channel 722 is combined with the outlet 724 to provide a flow path through the pressure side surface 330 at an angle substantially perpendicular (e.g., + / - 5° or + / - 10°) to the pressure side surface 330. In other words, the gas will be ejected from the outlet 724 at an angle substantially perpendicular to the working fluid F flowing through the pressure side surface 330. Fig.10 As shown, the outlet 724 may be formed as a plurality of rectangular openings through the pressure side surface 330. The rectangular openings are formed by ribs 726 extending through the outlets 724. In an alternative embodiment, the ribs 726 may stop short of reaching the outlets 724, such that the outlet 724 comprises a single continuous elongated radial opening through the pressure side surface 330, the radial length of which matches (i.e., is the same as or similar to) the radial length from one radial end of the aft cavity 420 to the opposite radial end of the aft cavity 420.

[0049] In an embodiment, gas flows into the rear cavity 420 through the rear inlet 421, flows from the rear cavity 420 into a plurality of rib-separated channels in the channel 722, and is ejected from the opening of the outlet 724 as a gas curtain that is substantially perpendicular to the pressure side surface 330. However, it should be understood that this is an example embodiment and other embodiments are possible. For example, in alternative embodiments, the ribs 726 may be omitted, the ribs 726 may extend less than the entire length of the channel 722, the outlet 724 may be formed as a single continuous elongated opening, the channel 722 and / or the outlet 724 may be configured to eject gas at a non-perpendicular angle relative to the pressure side surface 330, and / or the like.

[0050] Both the first and second embodiments of the nozzle vane 200 are shown with a front cavity 410 that supplies gas through the suction side surface 340 via a first path (i.e., including passage 412 and outlet 414), and a separate rear cavity 420 that supplies gas through the pressure side surface 330 via a second path (i.e., including passage 422 / 722 and outlet 424 / 724). However, in alternative embodiments, a single cavity may supply gas to both the first and second paths. In such a case, the nozzle vane 200 may include a single cavity in its core, and the first path through the suction side surface 340 and the second path through the pressure side surface 330 may extend from the same point or different points of the cavity (e.g., as straight or curved passages) to their respective outlets, which may be located at the same location as shown herein or at a different location than shown herein. Notably, in this alternative embodiment, the second path through the pressure side surface 330 may be implemented using the same passage 422 and outlet 424 (e.g., with or without ribs 426) or passage 722 and outlet 724 (e.g., with or without ribs 726) as described herein. On the other hand, depending on the shape and positioning of the cavity, the first path may be implemented differently, but may still include a curved or straight passage through the outlet 414 (e.g., with or without ribs).

[0051] In another alternative embodiment, each nozzle vane 200 may consist of only a single cavity, supplying gas through only a single surface via a single path. As yet another alternative embodiment, each nozzle vane 200 may consist of a single cavity, supplying gas through a single surface via two or more paths. As yet another alternative embodiment, each nozzle vane 200 may include two or more cavities, supplying gas through a single surface via two or more paths. In these cases, the single surface may be the pressure side surface 330 or the suction side surface 340. It should be understood that other configurations of one or more cavities and one or more injection points through one or more surfaces are also possible. Regardless of the specific configuration, each cavity can be shaped to produce a desired internal pressure gradient, as described elsewhere herein (e.g., via tapered surfaces 240, 418, or 428), and each path can include a channel (e.g., channel 412, 422, or 722) and an outlet (e.g., outlet 414, 424, or 724) that are configured to inject gas at a desired angle (e.g., substantially perpendicular to the mainstream through the nozzle, at a downstream angle that is non-perpendicular to the mainstream through the nozzle, etc.) to thereby affect the mainstream of the working fluid F through the nozzle, as described throughout the text.

[0052] Industrial Applicability

[0053] The nozzle includes a plurality of nozzle vanes that are equally spaced and arranged circumferentially about the longitudinal axis L. Instead of or in addition to using mechanically variable nozzle vanes, the disclosed embodiments utilize aerodynamically variable nozzle vanes to affect the flow of gas (e.g., working fluid F) through the nozzle (i.e., between the annularly arranged nozzle vanes). For example, such a nozzle may be included in the turbine 140 as a turbine stator assembly 144, such as a turbine stator assembly 144 in a first stage of the turbine 140. However, such a nozzle may alternatively or additionally be included in one or more subsequent stages of the stator assembly 144 in the turbine 140, and / or may be included in one or more stages of the stator assembly 124 in the compressor 120.

[0054] Each nozzle vane may include one or more cavities (e.g., 410, 420) at its core. Each cavity may include a tapered surface (e.g., 418, 428) shaped to produce a desired internal pressure gradient. For example, the tapered surface (e.g., 418, 428) may be shaped to produce an internal pressure gradient that matches an external pressure gradient along the radial span of the nozzle vane 200. Because the intensity of the ejected gas at the outlet (e.g., 414, 424, 724) is driven by the pressure difference between the inside and outside of each nozzle vane 200, the matching of the internal and external pressure gradients will produce an ejected gas curtain with uniform or constant intensity across the entire outlet (e.g., 414, 424, 724).

[0055] In order to utilize the limited internal geometry of the nozzle vane 200 for effective flow control, each cavity (e.g., 410, 420) may include a channel (e.g., 412, 422, 722) that creates a spray path from an outlet (e.g., 414, 424, 724) that is substantially perpendicular to the flow path through the nozzle. The outlet (e.g., 414, 424, 724) may be a single continuous radially elongated opening so that a continuous air curtain is sprayed perpendicularly across the radial span of each nozzle vane into the flow path through the nozzle. Such an outlet (e.g., 414, 424, 724) eliminates the need to form closely spaced straight circular holes through the surface of each nozzle vane 200, which may cause structural problems. To further alleviate structural problems, ribs (e.g., 416, 426, 726) may be provided within the channel (e.g., 412, 422, 722) to increase structural integrity.

[0056] Although the embodiments of the nozzle vane 200 are primarily described herein as using a destructive jet gas curtain to control the flow of a working fluid F through a nozzle (e.g., the flow of the working fluid F), the nozzle vane 200 having the same or similar structure may be used for other applications. For example, in an alternative application, in addition to or in lieu of disrupting the flow of the working fluid F through the nozzle, the nozzle vane 200 may be used to mix a coolant (e.g., gas bled from the compressor 120) into the working fluid F as the working fluid F flows through the nozzle. It should be understood that the angle at which the coolant is ejected from the outlet (e.g., 414, 424, 724) of each nozzle vane 200 and / or the position of the outlet (e.g., 414, 424, 724) may be set differently depending on the specific application, but all other features may remain substantially the same.

[0057] It should be understood that the above benefits and advantages may relate to one embodiment or may relate to several embodiments. Aspects described in conjunction with one embodiment are intended to be usable with other embodiments. Any explanation in conjunction with one embodiment applies to similar features of other embodiments, and elements of multiple embodiments may be combined to form other embodiments. The embodiments are not limited to embodiments that solve any or all of the problems described or embodiments that have any or all of the benefits and advantages described.

[0058] The foregoing detailed description is merely exemplary in nature and is not intended to limit the invention or the application and use of the invention. The described embodiments are not limited to use in conjunction with a particular type of machine. Therefore, although the present embodiment is depicted and described as being implemented in a gas turbine engine for ease of illustration, it should be understood that it can be implemented in various other types of turbomachinery and machines with turbine blades and in various other systems and environments. In addition, it is not intended to be limited by any theory presented in any of the preceding sections. It should also be understood that the illustrations may include exaggerated dimensions and graphic representations to better illustrate the referenced items shown, and are not to be considered limiting unless explicitly stated as such.

Claims

1. A nozzle blade (200), comprising: an inlet (210) through a first radial end of the nozzle vane; a cavity (220) within the core of the nozzle vane, the cavity extending from the inlet toward a second radial end of the nozzle vane, wherein a cross-sectional area of ​​the cavity (220) decreases from the first radial end to the second radial end along a radial axis of the nozzle vane; and An outlet (230) is formed through a side surface of the nozzle vane, the outlet being in fluid communication with the cavity. 2 . The nozzle vane of claim 1 , further comprising a passage between the cavity and the outlet, the passage forming a flow path through the outlet, wherein the flow path through the outlet is substantially perpendicular to the side surface.

3. The nozzle vane according to claim 2, wherein: The channel includes a plurality of ribs separated along the radial axis, the ribs dividing at least a portion of the channel into a plurality of channels.

4. The nozzle vane according to claim 2, wherein: The passage extends from a rear portion of the cavity and curves toward the outlet.

5. The nozzle vane according to claim 2, wherein: The passage extends from the rear of the cavity toward the rear edge of the nozzle, with the rear end of the passage emerging from the outlet.

6. The nozzle vane of claim 5, further comprising a plurality of ribs spaced apart along the radial axis, the ribs dividing at least a portion of the passage into a plurality of passages and dividing the outlet into a plurality of openings.

7. The nozzle vane according to claim 1, wherein: The outlet consists of a single continuous elongated opening having a radial length matching the length of the cavity from the first radial end to the second radial end.

8. The nozzle vane of claim 1, further comprising a plurality of said cavities and a plurality of said outlets, each of said plurality of outlets being in fluid communication with a respective one of said plurality of cavities.

9. The nozzle vane according to claim 8, wherein: The plurality of outlets include a first outlet through a suction side surface of the nozzle vane and a second outlet through a pressure side surface of the nozzle vane.

10. The nozzle vane according to claim 8, wherein: The plurality of cavities include a front cavity located in front of the nozzle vane and a rear cavity located in rear of the nozzle vane.

11. The nozzle vane according to claim 10, wherein: The plurality of outlets include a front outlet passing through a suction side surface of the nozzle vane and in fluid communication with the front cavity, and an aft outlet passing through a pressure side surface of the nozzle vane and in fluid communication with the aft cavity.

12. The nozzle vane of claim 11, further comprising: a front passage between the front cavity and the front outlet, the front passage forming a flow path through the front outlet, wherein the flow path through the front outlet is substantially perpendicular to the suction side surface; as well as An aft passage is located between the aft cavity and the aft outlet, the aft passage forming a flow path through the aft outlet, wherein the flow path through the aft outlet is substantially perpendicular to the pressure side surface.

13. The nozzle vane of claim 1, wherein: The outlet passes through a suction side surface of the nozzle vane.

14. The nozzle vane of claim 1, wherein: The outlet passes through a pressure side surface of the nozzle vane.

15. A nozzle vane (200), comprising: a forward inlet (210) through a first radial end of the nozzle vane; a forward cavity (410) within the core of the nozzle vane, the forward cavity extending from the forward inlet toward a second radial end of the nozzle vane, wherein a cross-sectional area of ​​the forward cavity decreases along a radial axis of the nozzle vane from the first radial end to the second radial end; a forward outlet (414) through a suction side surface of the nozzle vane; a front passage (412) connecting the front cavity to the front outlet; a rear inlet through the first radial end of the nozzle vane; a rear cavity (420) within the core of the nozzle vane, the rear cavity extending from the rear inlet toward the second radial end, wherein a cross-sectional area of ​​the rear cavity decreases along the radial axis from the first radial end to the second radial end; a rear outlet (424) through a pressure side surface of the nozzle vane; and A rear passage (426) connects the rear cavity to the rear outlet.

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