Patent Application
20230313690
Internal components of gas turbine engines, especially those in the hot combustion gas path, are exposed to temperatures of approximately 900° C. or hotter. Blades and vanes in the turbine section of the gas turbine engine are among these internal components. The high temperatures often cause damage to the components, so the components are designed to utilize various cooling schemes to cool the surfaces of the blades and vanes that are exposed to the hot combustion gases. For example, blades and vanes are often constructed of high temperature superalloys coated with barrier coatings that can withstand the high temperatures. Additionally, the superalloy components often include cooling passages terminating on the component outer surface for passage of coolant fluid to cool the surfaces exposed to the hot combustion gases.
In one construction, a gas turbine blade includes a root for connecting to a rotor of a gas turbine engine, a platform attached to the root and defining a groove, a platform impingement plate, and an airfoil. The platform impingement plate includes a circumferential edge surrounding a cavity, the edge positioned to contact a first surface of 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. The plate surface includes at least one impingement hole through which a fluid flow flows to cool the first surface of the platform. Each end portion extends beyond the plate surface and includes a curvature so that the curved end portion is inserted into the groove. The airfoil includes a metallic substrate extending from a second surface of the platform opposite the first surface to a tip, the airfoil including a pressure side and a suction side, the pressure side and the suction side meeting at a trailing edge and a leading edge.
In another construction, a gas turbine blade includes a root for connecting to a rotor of a gas turbine engine, a platform attached to the root defining a side surface and a groove formed in the side surface, a platform sealing wire positioned in the groove, and an airfoil including a metallic substrate extending from a surface of the platform to a tip, the airfoil including a pressure side and a suction side, the pressure side and the suction side meeting at a trailing edge and a leading edge. The sealing wire includes a first curved portion and a second flat portion so that the platform sealing wire has a D-shaped cross section.
To easily identify the discussion of any particular element or act, the most significant digit or digits in a reference number refer to the figure number in which that element is first introduced.
Before any embodiments of the invention are explained in detail, it is to be understood that the invention is not limited in its application to the details of construction and the arrangement of components set forth in this description or illustrated in the following drawings. The invention is capable of other embodiments and of being practiced or of being carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.
Various technologies that pertain to systems and methods will now be described with reference to the drawings, where like reference numerals represent like elements throughout. The drawings discussed below, and the various embodiments used to describe the principles of the present disclosure in this patent document are by way of illustration only and should not be construed in any way to limit the scope of the disclosure. Those skilled in the art will understand that the principles of the present disclosure may be implemented in any suitably arranged apparatus. It is to be understood that functionality that is described as being carried out by certain system elements may be performed by multiple elements. Similarly, for instance, an element may be configured to perform functionality that is described as being carried out by multiple elements. The numerous innovative teachings of the present application will be described with reference to exemplary non-limiting embodiments.
Also, it should be understood that the words or phrases used herein should be construed broadly, unless expressly limited in some examples. For example, the terms “including,” “having,” and “comprising,” as well as derivatives thereof, mean inclusion without limitation. The singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. Further, the term “and/or” as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items. The term “or” is inclusive, meaning and/or, unless the context clearly indicates otherwise. The phrases “associated with” and “associated therewith,” as well as derivatives thereof, may mean to include, be included within, interconnect with, contain, be contained within, connect to or with, couple to or with, be communicable with, cooperate with, interleave, juxtapose, be proximate to, be bound to or with, have, have a property of, or the like. Furthermore, while multiple embodiments or constructions may be described herein, any features, methods, steps, components, etc. described with regard to one embodiment are equally applicable to other embodiments absent a specific statement to the contrary.
Also, although the terms “first”, “second”, “third” and so forth may be used herein to refer to various elements, information, functions, or acts, these elements, information, functions, or acts should not be limited by these terms. Rather these numeral adjectives are used to distinguish different elements, information, functions or acts from each other. For example, a first element, information, function, or act could be termed a second element, information, function, or act, and, similarly, a second element, information, function, or act could be termed a first element, information, function, or act, without departing from the scope of the present disclosure.
In addition, the term “adjacent to” may mean: that an element is relatively near to but not in contact with a further element; or that the element is in contact with the further portion, unless the context clearly indicates otherwise. Further, the phrase “based on” is intended to mean “based, at least in part, on” unless explicitly stated otherwise. Terms “about” or “substantially” or like terms are intended to cover variations in a value that are within normal industry manufacturing tolerances for that dimension. If no industry standard is available, a variation of twenty percent would fall within the meaning of these terms unless otherwise stated.
The compressor section 104 is in fluid communication with an inlet section 116 to allow the gas turbine engine 100 to draw atmospheric air into the compressor section 104. During operation of the gas turbine engine 100, the compressor section 104 draws in atmospheric air and compresses that air for delivery to the combustion section 102. The illustrated compressor section 104 is an example of one compressor section 104 with other arrangements and designs being possible.
In the illustrated construction, the combustion section 102 includes a plurality of separate combustors 112 that each operate to mix a flow of fuel with the compressed air from the compressor section 104 and to combust that air-fuel mixture to produce a flow of high temperature, high pressure combustion gases or exhaust gas 118. Of course, many other arrangements of the combustion section 102 are possible.
The turbine section 106 includes a plurality of turbine stages 110 with each turbine stage 110 including a number of rotating turbine blades 126 and a number of stationary blades or vanes. The turbine stages 110 are arranged to receive the exhaust gas 118 from the combustion section 102 at a turbine inlet 114 and expand that gas to convert thermal and pressure energy into rotating or mechanical work. The turbine section 106 is connected to the compressor section 104 to drive the compressor section 104. For gas turbine engines 100 used for power generation or as prime movers, the turbine section 106 is also connected to a generator, pump, or other device to be driven. As with the compressor section 104, other designs and arrangements of the turbine section 106 are possible.
A control system 120 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and to control various operations of the gas turbine engine 100. In preferred constructions the control system 120 is typically micro-processor based and includes memory devices and data storage devices for collecting, analyzing, and storing data. In addition, the control system 120 provides output data to various devices including monitors, printers, indicators, and the like that allow users to interface with the control system 120 to provide inputs or adjustments. In the example of a power generation system, a user may input a power output set point and the control system 120 may adjust the various control inputs to achieve that power output in an efficient manner.
The control system 120 can control various operating parameters including, but not limited to variable inlet guide vane positions, fuel flow rates and pressures, engine speed, valve positions, 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 assure that the gas turbine engine 100 is operating properly. Some parameters that are monitored may include inlet air temperature, compressor outlet temperature and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, and the like. Many of these measurements are displayed for the user and are logged for later review should such a review be necessary.
In an embodiment, the platform impingement plate 212 is additively manufactured. Additive Manufacturing (AM) enables the manufacturing of components that are difficult to manufacture using conventional manufacturing techniques such as the curved ends of the flat member 408.
Turbine engine internal components, such as the turbine blade 126 shown in
Although an exemplary embodiment of the present disclosure has been described in detail, those skilled in the art will understand that various changes, substitutions, variations, and improvements disclosed herein may be made without departing from the spirit and scope of the disclosure in its broadest form.
None of the description in the present application should be read as implying that any particular element, step, act, or function is an essential element, which must be included in the claim scope: the scope of patented subject matter is defined only by the allowed claims. Moreover, none of these claims are intended to invoke a means plus function claim construction unless the exact words “means for” are followed by a participle.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/US2021/046709 | 8/19/2021 | WO |
| Number | Date | Country | |
|---|---|---|---|
| 63074786 | Sep 2020 | US | |
| 62706535 | Aug 2020 | US |
