Gas turbine blade

Abstract

A gas turbine blade comprising a root for connecting to a rotor of a gas turbine, a platform attached to the root, the platform defining a side surface and a recess formed in the side surface, and an airfoil comprising a metal substrate extending from a surface of the platform to a tip, the airfoil comprising a pressure side and a suction side meeting at a trailing edge and a leading edge, and a platform strike plate. The platform strike plate comprising a circumferential edge around a cavity, the edge positioned to contact the platform, a plate surface positioned to form the cavity between the first surface and the plate surface, and a flat member having a face attached to the plate surface and at least one end portion. A gas turbine blade comprising a platform seal line positioned in the recess of the platform is also provided.

Description

Background Technology

[0001] Internal components of gas turbine engines, especially those in the hot combustion gas path, are exposed to temperatures of approximately 900 degrees Celsius or higher. Blades and impellers in the turbine section of a gas turbine engine are among these internal components. High temperatures can typically damage these components, so they are designed to utilize various cooling methods to cool the surfaces of blades and impellers exposed to hot combustion gases. For example, blades and impellers are often made of high-temperature superalloys with a high-temperature-resistant barrier coating. Furthermore, superalloy components typically include cooling channels terminating on the outer surface of the component, which allow cooling fluid to pass through and thus cool the surfaces exposed to hot combustion gases. Summary of the Invention

[0002] In one configuration, a gas turbine blade includes: a root for connection to a rotor of a gas turbine engine; a platform connected to the root and defining a recess; a platform impact plate; and an airfoil. The platform impact plate includes: a circumferential edge surrounding the cavity, positioned to contact a first surface of the platform; a plate surface positioned to form a cavity between the first surface and the plate surface; and a flat member having a face attached to the plate surface and at least one end portion. The plate surface includes at least one impact hole through which fluid flows to cool the first surface of the platform. Each end portion extends beyond the plate surface and includes a curvature such that the curved end portion inserts into the recess. The airfoil includes a metal base extending from a second surface of the platform opposite to the first surface to a tip, the airfoil including a pressure side and an intake side, the pressure side and the intake side abutting at a trailing edge and a leading edge.

[0003] In another configuration, the gas turbine blade includes: a root for connection to a rotor of a gas turbine engine; a platform attached to the root, defining a side surface and a groove formed therein; a platform seal line positioned within the groove; and an airfoil including a metal base extending from the surface of the platform to a tip, the airfoil including a pressure side and an intake side, the pressure side and the intake side abutting at a trailing edge and a leading edge. The seal line includes a first curved portion and a second flat portion, such that the platform seal line has a D-shaped cross-section. Attached Figure Description

[0004] To facilitate the identification of any particular element or action under discussion, one or more of the most important numbers in the reference numerals refer to the drawing number in which the element was first introduced.

[0005] Figure 1 This is a longitudinal cross-sectional view of a gas turbine engine taken along a plane containing the longitudinal axis or the central axis.

[0006] Figure 2 This is a perspective view of the turbine blades, including the platform impact plate.

[0007] Figure 3 Another perspective view of the turbine blades, including the platform impact plate.

[0008] Figure 4 This is a 3D view of the platform impact plate.

[0009] Figure 5 This is a perspective view of the turbine blades, including the orifice plate.

[0010] Figure 6 This is a three-dimensional view of the orifice plate.

[0011] Figure 7 The illustration shows a partial side view of the platform and its trailing edge.

[0012] Figure 8 A perspective view of a turbine blade with a coating.

[0013] Figure 9 This is a partial perspective view of a turbine blade with a sealing line.

[0014] Figure 10 This is a 3D view of the sealing line.

[0015] Figure 11 This is a three-dimensional view of the turbine blades and their adjacent guide impellers. Detailed Implementation

[0016] Before detailing any embodiments of the invention, it should be understood that the invention is not limited in its application to the details of the structure and arrangement of the components set forth in this description or shown in the following drawings. The invention can have other embodiments and can be practiced or implemented in various ways. Furthermore, it should be understood that the wording and terminology used herein are for descriptive purposes and should not be considered limiting.

[0017] Various techniques relating to systems and methods will now be described with reference to the accompanying drawings, wherein similar reference numerals always denote similar elements. The drawings discussed below in this patent document, as well as the various embodiments used to describe the principles of this disclosure, are merely illustrative and should not be construed in any way as limiting the scope of this disclosure. Those skilled in the art will understand that the principles of this disclosure can be implemented with any suitably arranged device. It is to be understood that functions described as being performed by certain system elements can be performed by multiple elements. Similarly, for example, elements can be configured to perform functions described as being performed by multiple elements. Numerous inventive teachings of this application will be described with reference to exemplary, non-limiting embodiments.

[0018] Furthermore, it should be understood that, unless explicitly limited in some examples, the words or phrases used herein should be interpreted broadly. For example, the terms “comprising,” “having,” and “including,” and their derivatives, mean non-restrictive inclusion. Unless the context explicitly indicates otherwise, the singular forms “a,” “an,” and “the” are also intended to include the plural forms. Additionally, the term “and / or” as used herein refers to and includes any and all possible combinations of one or more associated listed items. Unless the context explicitly indicates otherwise, the term “or” is inclusive, meaning and / or. The phrases “associated with” and “related to,” and their derivatives, can mean including, being included in, interconnected with, containing, contained within, connected to or connected with, linked to or connected with, communicable with, cooperating with, intertwined, juxtaposed, proximate, combined with or combined with, having, possessing the properties of, etc. Furthermore, although multiple embodiments or structures may be described herein, any features, methods, steps, components, etc., described with respect to one embodiment apply equally to other embodiments unless otherwise specifically stated otherwise.

[0019] Furthermore, although the terms “first,” “second,” “third,” etc., may be used herein to refer to various elements, information, functions, or actions, these elements, information, functions, or actions should not be limited by these terms. Rather, these numerical adjectives are used to distinguish different elements, information, functions, or actions from one another. For example, without departing from the scope of this disclosure, a first element, first information, first function, or first action may be referred to as a second element, second information, second function, or second action, and similarly, a second element, second information, second function, or second action may be referred to as a first element, first information, first function, or first action.

[0020] Additionally, unless the context explicitly indicates otherwise, the term "adjacent to" can mean: an element is fairly close to another element but not in contact with it; or an element is in contact with another part. Furthermore, unless explicitly stated otherwise, the phrase "based on" is intended to mean "at least partially based on". The terms "approximately" or "roughly" or similar terms are intended to cover variations in values ​​within the normal industrial manufacturing tolerance range used for that dimension. In the absence of an available industry standard, unless otherwise stated, twenty percent of the variation will fall within the meaning of these terms.

[0021] Figure 1An example of a gas turbine engine 100 is shown, comprising a compression section 104, a combustion section 102, and a turbine section 106 arranged along a central axis 122. The compression section 104 includes multiple compression stages 108, each of which includes a set of turbine blades 126 and a set of stationary blades 124 or adjustable guide impellers. A rotor 128 supports the turbine blades 126 for rotation about the central axis 122 during operation. In some configurations, a single integral rotor 128 extends the length of the gas turbine engine 100 and is supported for rotation by bearings at either end. In other configurations, the rotor 128 is assembled from several separate spools attached to each other, or may include multiple disc sections attached via bolts or bolts.

[0022] The compression section 104 is in fluid communication with the inlet section 116 to allow the gas turbine engine 100 to draw atmospheric air into the compression section 104. During operation of the gas turbine engine 100, the compression section 104 draws in atmospheric air and compresses it for delivery to the combustion section 102. The compression section 104 shown is an example of a compression section 104; other arrangements and designs are also possible.

[0023] In the illustrated configuration, the combustion section 102 includes a plurality of individual burners 112, each of which operates to mix and burn the fuel stream with compressed air from the compression section 104, thereby producing a high-temperature, high-pressure combustion gas stream or exhaust gas stream 118. Of course, many other arrangements of the combustion section 102 are possible.

[0024] Turbine section 106 includes multiple turbine stages 110, each turbine stage 110 including multiple rotating turbine blades 126 and multiple stationary blades or impellers. Turbine stages 110 are arranged to receive exhaust gas 118 from combustion section 102 at turbine inlet 114 and expand the gas to convert thermal and pressure energy into rotational or mechanical work. Turbine section 106 is connected to compression section 104 to drive compression section 104. For a gas turbine engine 100 used for power generation or as a prime mover, turbine section 106 is also connected to a generator, pump, or other device to be driven. Similar to compression section 104, other designs and arrangements of turbine section 106 are possible.

[0025] The control system 120 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and control various operations of the gas turbine engine 100. In a preferred configuration, the control system 120 is typically microprocessor-based and includes memory devices and data storage devices for collecting, analyzing, and storing data. Additionally, the control system 120 provides output data to various devices, including monitors, printers, indicators, etc., that allow users to interact with the control system 120 to provide input or adjustment. In the example of a power generation system, the user can input a power output setpoint, and the control system 120 can adjust various control inputs to achieve that power output efficiently.

[0026] The control system 120 can control various operating parameters, including but not limited to variable inlet guide impeller position, fuel flow rate and pressure, engine speed, valve position, generator load, and generator excitation. Of course, other applications may have fewer or more controllable devices. The control system 120 also monitors various parameters to ensure proper operation of the gas turbine engine 100. Some of the monitored parameters may include inlet air temperature, compressor outlet temperature and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, etc. Many of these measurements are displayed to the user and recorded for subsequent review if necessary.

[0027] Figure 2 A perspective view of a turbine blade 126, which may be found in a gas turbine engine 100, is illustrated. The turbine blade 126 includes an airfoil 202, a platform 204, and a root 206. The root 206 may be connected to the rotor 128 of the gas turbine engine 100. The platform 204 is formed radially outward at the root 206 and is located between the root 206 and the airfoil 202. The airfoil 202 is attached to the platform 204 and extends radially outward from the platform 204 to a tip 218. The airfoil 202 includes an outer surface having a pressure side 214 and an intake side 216. The pressure side 214 and the intake side are abutted at an upstream leading edge 210 and a downstream trailing edge 208. The terms "leading" and "trailing" are used in relation to the fluid flow of the working flow of the gas turbine engine 100. In one embodiment, Figure 2 The image shows the platform impact plate 212 located on the side of the platform 204 facing the root 206 and opposite to the airfoil 202.

[0028] Figure 3Another view of the platform impact plate 212 is shown. The platform impact plate 212 is attached to a first surface of the platform facing the root 206, and also to a surface opposite to the platform surface from which the airfoil 202 extends. Furthermore, the platform impact plate 212 is located on the pressure side 214 of the turbine blade 126.

[0029] Figure 4 A perspective top view of a platform impact plate 212 is shown. The platform impact plate 212 includes a circumferential edge 404 that contacts and attaches to a first surface of a platform 204. The circumferential edge 404 is in continuous contact with the first surface of the platform 204. The edge 404 surrounds a cavity 406 defined by a plate surface 410 and the surrounding edge 404. The plate surface 410 may include at least one impact hole 402. In one embodiment, the plate surface 410 includes more than one impact hole 402. The impact holes 402 allow fluid flow to cool the first surface of the platform. The platform impact plate 212 includes a flat member 408 having a surface attached to the plate surface 410. The flat member 408 includes at least one end portion extending beyond the plate surface 410 and including a curved end. The curved end fits into a recess in the platform 204. Figure 4 The illustrated embodiment includes a flat member 408 having two end portions, each end portion including a curved end. Each of the curved ends is fitted into a corresponding recess in the platform 204, such that the platform impact plate 212 can be attached to the platform 204. In one embodiment, the curved end is slightly larger than the recess, such that the curved end deforms slightly when it is installed to hold the platform impact plate 212 in place.

[0030] In one embodiment, the platform impact plate 212 is additively manufactured. Additive manufacturing (AM) enables the production of components that are difficult to manufacture using conventional manufacturing techniques, such as the curved ends of the flat member 408.

[0031] Figure 5 A perspective view of a turbine blade 126 is shown, the vortex blade being observed such that the bottom of the root 206 is visible. The bottom surface of the root 206 includes at least one root cavity 504. Figure 5 In the embodiment of the turbine blade 126 shown, the root 206 includes three root cavities 504. Figure 5 In the rightmost root cavity 504, the orifice plate 502 is shown as a plate having an opening that covers the entrance into the root cavity 504.

[0032] Figure 6 It shows Figure 5A perspective view of the orifice plate 502 shown in the root cavity 504 of the root portion 206. The orifice plate 502 includes a plate 602 having at least one orifice 606. In the illustrated embodiment, the plate 602 has an octagonal shape. At least one insertion plate 604 extends from a first surface of the plate 602. Figure 6 In one embodiment, two insert plates 604 extend from a first surface of plate 602. The insert plates 604 can be inserted into a root cavity 504, where they are fitted into the root cavity 504. In one embodiment, plate 602 may include at least one fin 608 extending from a second surface of plate 602 opposite to the first surface.

[0033] Figure 7 The illustration shows platform 204 at the trailing edge 208. Platform 204 on the trailing edge side extends to the end of trailing edge 208, allowing platform 204 to be shorter than conventional turbine blades. The shorter platform 204 is easier to cool and prevents oxidation and TBC damage.

[0034] Turbine engine internal components, such as Figure 8 The turbine blade 126 shown typically includes a thermal barrier coating (TBC) of metal-ceramic material, which is applied directly to the outer surface of the component substrate or over an intermediate metal-bonded coating previously applied to the substrate surface. The TBC provides an insulating layer on the component substrate, which reduces the substrate temperature. Figure 8 The image includes a perspective view of a turbine blade 126 having a thermal protection system 802, which may include a bonding coating applied to a substrate. The thermal protection system 802 may also include a thermal barrier coating applied over the bonding coating as a top coating. In an alternative embodiment, the thermal barrier coating is applied directly to the metal substrate. In one embodiment, the thermal protection system 802 is applied to a portion of the airfoil 202 and / or to the platform 204. For example, the bonding coating may be applied to the entire airfoil substrate, including the tip 218, leading edge 210, trailing edge 208, intake side 216, and pressure side 214. The bonding coating may be applied to the platform 204. The surfaces to which the bonding coating is applied may include surfaces represented by A, B, C, and D. In one embodiment, the bonding coating comprises a platinum-aluminum alloy (PtAl). The top coating may be applied to the bonding coating on the portion of the airfoil 202 and the platform 204 using an electron beam physical vapor deposition (EBPVD) process. In one embodiment, the top coating is applied to the tip 218, pressure side 214, suction side 216, and leading edge 210, but not to the trailing edge 208. The thermal protection system 802, the PtAl bonded coating, and the EBPVD top coating have a better surface finish than air plasma spraying (APS) coatings, thus achieving an efficiency advantage.

[0035] Figure 9A partial perspective view of a turbine blade 126 with a sealing line 902 is shown. Figure 9 The turbine blade 126 includes a platform 204, which includes a side surface 904, wherein a groove is formed in the side surface 904. Figure 10 As shown, the sealing line 902 includes a first curved portion and a second flat portion, such that the sealing line 902 has a D-shaped cross-section. The sealing line 902 is oriented such that the second flat portion faces the inner diameter of the gas turbine engine. Using a sealing line instead of a sealing strip as previously used requires less machining for installation within the platform 204 and includes the advantages of dynamic damping. Specifically, the sealing line 902 is compressed between two adjacent turbine blades 126 and is elastic, thereby reducing vibration between the turbine blades 126.

[0036] Figure 11 The illustration shows a turbine blade 126 with a platform 204 having a damping cavity 1102 on its trailing edge side. The damping cavity 1102 receives the leading edge portion 1106 of the adjacent guide impeller 1104 of the next stage. During operation of the gas turbine engine 100, the interaction between the leading edge portion 1106 and the damping cavity 1102 reduces vibration. The adjacent guide impeller 1104 includes a T-shaped platform 1108, which reduces the intake of hot gas into the platform cavity.

[0037] Although exemplary embodiments of the present disclosure have been described in detail, those skilled in the art will understand that various modifications, substitutions, variations and improvements can be made to the content disclosed herein without departing from the spirit and scope of the widest form of the disclosure.

[0038] Nothing described in this application should be construed as implying that any particular element, step, action, or function is a necessary element that must be included within the scope of the claims: the scope of the patent subject matter is defined only by the permitted claims. Furthermore, unless the exact phrase "means for..." is followed by a participle, these claims are not intended to invoke a means-plus-function claim structure.

Claims

1. A gas turbine blade, comprising: The root, which is used to connect to the rotor of the gas turbine engine; Platform, the platform being attached to the root and defining a groove; Platform impact plate, including: A circumferential edge surrounding the cavity, the edge being positioned to contact a first surface of the platform, a plate surface, the plate surface being positioned to form the cavity between the first surface and the plate surface, and A flat member having a face attached to the plate surface and at least one end portion, wherein each end portion extends beyond the plate surface and includes a curvature such that the curved end portion is inserted into the groove; and An airfoil comprising a metal base extending from a second surface opposite to the first surface of the platform to a tip, the airfoil comprising a pressure side and an intake side, the pressure side and the intake side being joined at a trailing edge and a leading edge, respectively. The plate surface includes at least one impact hole, through which fluid flows to cool the first surface of the platform. The airfoil further includes a thermal protection system deposited on the substrate, the thermal protection system comprising a thermal barrier coating and a bonding coating applied to the metal substrate, the thermal barrier coating comprising an EBPVD top coating applied on the bonding coating to a portion of the airfoil, and The platform further includes a thermal protection system deposited on the second surface, the thermal protection system including a thermal barrier coating and a bonding coating applied to the second surface, the thermal barrier coating including an EBPVD top coating applied on the bonding coating.

2. The gas turbine blade according to claim 1, wherein, The platform impact plate contacts the first surface on the pressure side of the turbine blade.

3. The gas turbine blade according to claim 1, wherein, The platform impact plate is additively manufactured.

4. The gas turbine blade according to claim 1, wherein, The root portion defines a cavity, and wherein the orifice plate includes a plate containing an orifice and at least one insert plate, the insert plate being fitted into the cavity in the root portion such that the plate covers the cavity.

5. The gas turbine blade according to claim 1, wherein, The orifice plate is octagonal.

6. The gas turbine blade according to claim 1, wherein, The bonding coating comprises PtAl.

7. The gas turbine blade according to claim 1, wherein, The portion of the airfoil includes the intake side, the pressure side, the tip, and the leading edge.

8. The gas turbine blade according to claim 7, wherein, The bonding coating comprises PtAl.

9. The gas turbine blade according to claim 1, wherein, The platform extends to the trailing edge on the trailing edge side of the platform.

10. A method for repairing a gas turbine engine having blades according to one or more of claims 1 to 9, the method comprising: The blades are mounted onto the rotor.

11. The method according to claim 10, wherein, The blades are mounted such that a damping cavity on the trailing edge side of the blade platform receives the leading edge portion of an adjacent guide impeller, and wherein the guide impeller has a T-shaped platform, thereby reducing vibration through the interaction between the leading edge portion and the damping cavity during operation of the gas turbine engine.

12. The method of claim 11, further comprising: The guide impeller is installed onto the stator of the gas turbine engine.

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