Patent Grant
12018591
A gas turbine engine typically includes a compressor section, a turbine section, and a combustion section disposed therebetween. The compressor section includes multiple stages of rotating compressor blades and stationary compressor vanes. The combustion section typically includes a plurality of combustors. The turbine section includes multiple stages of rotating turbine blades and stationary turbine vanes. Turbine blades and vanes often operate in a high temperature environment and are internally cooled. The combustor may include fuel injectors for providing a fuel to be mixed with compressed air from the compressor section and an ignition source for igniting the mixture to form hot exhaust gas for the turbine section.
In one aspect, a ring segment assembly includes a ring segment including an impingement pocket having an impingement surface, a plurality of pins extending from the impingement surface, the plurality of pins are arranged to define a plurality of pinless impingement areas, and an impingement plate spaced a non-zero distance from the impingement surface, the impingement plate having a plurality of bumps and a plurality of valleys, the impingement plate defining a plurality of impingement holes, each impingement hole of the plurality of impingement holes formed in one of the valleys of the plurality of valleys and positioned opposite one of the plurality of pinless impingement areas.
In one aspect, a ring segment assembly includes a ring segment including an impingement pocket having an impingement surface, a plurality of pins extending from the impingement surface, and an impingement plate spaced a non-zero distance from the impingement surface, the impingement plate having a plurality of bumps and a plurality of valleys arranged in an array having a plurality of rows and a plurality of columns, each bump of the plurality of bumps and each valley of the plurality of valleys alternating with each other in each row of the plurality of rows and each column of the plurality of columns, the impingement plate defining a plurality of impingement holes, each impingement hole of the plurality of impingement holes formed in one of the valleys of the plurality of valleys.
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.
Also, in the description, the terms “axial” or “axially” refer to a direction along a longitudinal axis of a gas turbine engine. The terms “radial” or “radially” refer to a direction perpendicular to the longitudinal axis of the gas turbine engine. The terms “downstream” or “aft” refer to a direction along a flow direction. The terms “upstream” or “forward” refer to a direction against the flow direction.
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 102 is in fluid communication with an inlet section 108 to allow the gas turbine engine 100 to draw atmospheric air into the compressor section 102. During operation of the gas turbine engine 100, the compressor section 102 draws in atmospheric air and compresses that air for delivery to the combustion section 104. The illustrated compressor section 102 is an example of one compressor section 102 with other arrangements and designs being possible.
In the illustrated construction, the combustion section 104 includes a plurality of separate combustors 120 that each operate to mix a flow of fuel with the compressed air from the compressor section 102 and to combust that air-fuel mixture to produce a flow of high temperature, high pressure combustion gases or exhaust gas 122. Of course, many other arrangements of the combustion section 104 are possible.
The turbine section 106 includes a plurality of turbine stages 124 with each turbine stage 124 including a number of stationary turbine vanes 126 and a number of rotating turbine blades 128. The turbine stages 124 are arranged to receive the exhaust gas 122 from the combustion section 104 at a turbine inlet 130 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 102 to drive the compressor section 102. 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 102, other designs and arrangements of the turbine section 106 are possible.
An exhaust portion 110 is positioned downstream of the turbine section 106 and is arranged to receive the expanded flow of exhaust gas 122 from the final turbine stage 124 in the turbine section 106. The exhaust portion 110 is arranged to efficiently direct the exhaust gas 122 away from the turbine section 106 to assure efficient operation of the turbine section 106. Many variations and design differences are possible in the exhaust portion 110. As such, the illustrated exhaust portion 110 is but one example of those variations.
A control system 132 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 132 is typically micro-processor based and includes memory devices and data storage devices for collecting, analyzing, and storing data. In addition, the control system 132 provides output data to various devices including monitors, printers, indicators, and the like that allow users to interface with the control system 132 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 132 may adjust the various control inputs to achieve that power output in an efficient manner.
The control system 132 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 132 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.
The ring segment assembly 200 includes a ring segment 202 and an impingement plate 204 that is fixedly connected to the ring segment 202. The ring segment 202 may be welded to the ring segment 202. Other connecting methods may also be used to connect the impingement plate 204 to the ring segment 202.
The ring segment 202 includes an impingement pocket 318 that is defined between the forward rail 306, the aft rail 308, the first mate face side 314, and the second mate face side 316. The impingement pocket 318 has an opening on the first side 302 that is covered by the impingement plate 204 (shown in
The plurality of pins 402 are arranged to form a plurality of pinless impingement areas 404 on the impingement surface 320. Each pinless impingement area 404 of the plurality of pinless impingement areas 404 is an area on the impingement surface 320 that includes no pins 402. Edges of each pinless impingement area 404 of the plurality of pinless impingement areas 404 are formed by a number of pins 402.
The plurality of pinless impingement areas 404 are arranged in rows along the X direction and in columns along the Y direction. At least one pin 402 is placed between two adjacent pinless impingement areas 404 in the rows. At least one pin 402 is placed between two adjacent pinless impingement areas 404 in the columns. A portion of the pinless impingement areas 404 has a hexagonal shape that is defined by the arrangement of pins 402 that surround the pinless impingement area 404. A remaining portion of the pinless impingement areas 404 has a parallelogram shape that is also defined by the arrangement of pins 402 that surround the pinless impingement area 404. The pinless impingement areas 404 have the same shape in the same rows and/or in the same columns. The pinless impingement areas 404 having the hexagonal shape reside in common rows and columns as do the parallelogram shaped pinless impingement areas 404. The rows and columns alternate and the pinless impingement areas 404 of adjacent rows and columns are offset from one another in a manner similar to that described with regard to the rows and columns of pins 402. In other constructions, the pinless impingement areas 404 may have any other different shapes, or arranged in any other different ways.
The foregoing dimensions illustrate some possible arrangements of the pins 402 with other constructions being possible. In other constructions, the pins 402 may have different dimensions.
The impingement plate 204 includes a plurality of bumps 602 and a plurality of valleys 604. The plurality of valleys 604 extend out from the impingement plate 204 toward the impingement surface 320 of the impingement pocket 318. The plurality of bumps 602 extend from the impingement plate 204 in an opposite direction from the plurality of valleys 604. The plurality of bumps 602 and the plurality of valleys 604 are arranged in an array having a plurality of rows along the X direction and a plurality of columns along the Y direction. The plurality of bumps 602 and the plurality of valleys 604 alternate to each other in each row of the plurality of rows and in each column of the plurality of columns. The plurality of bumps 602 and the plurality of valleys 604 are offset in each row and column defining a staggered arrangement. The plurality of bumps 602 and the plurality of valleys 604 provide a negative Poisson's Ratio structure to the impingement plate 204. Poisson's ratio is a measure of Poisson effect in which a material expands in a direction perpendicular to a direction of compression. The material that characterizes this behavior is defined as having a positive Poisson's Ration structure. On the other hand, a material with a negative Poisson's Ratio structure expands in a direction perpendicular to a direction of expansion. The material with negative Poisson's Ratio structure also contracts in a direction perpendicular to a direction of compression.
The impingement plate 204 includes a plurality of impingement holes 606. Each impingement hole 606 of the plurality of impingement holes 606 is formed in an associated valley 604 of the plurality of valleys 604.
The plurality of impingement holes 606 are formed in every other row and every other column of the plurality of valleys 604. Each impingement hole 606 is formed in an associated valley 604 at a position that is closest to the impingement surface 320. Each impingement hole 606 is positioned opposite to and associated with one pinless impingement area 404. Each impingement hole 606 defines a central axis 704 that is normal to the impingement surface 320 and passes through the associate pinless impingement area 404. In the illustrated construction, the central axis 704 passes through a center of the associate pinless impingement area 404. In other constructions, the central axis 704 may pass through the associated pinless impingement area 404 offset from the center.
In operation, a cooling flow 706 passes through each impingement hole 606 and impinges on each pinless impingement area 404 on the impingement surface 320. The cooling flow 706 travels the shortest distance from the impingement plate 204 to the impingement surface 320 which enhances heat transfer. The pinless impingement areas 404 allows undisturbed impingement on the pinless impingement areas 404 from the cooling flow 706. The undisturbed impingement improves heat transfer at the pinless impingement areas 404. The cooling flow 706 is disturbed by the plurality of pins 402. The pins 402 create turbulent flow which improves heat transfer coefficient and increase heat transfer areas. The enhanced heat transfer reduces requirement of the cooling flow 706 and thus improves performance of the gas turbine engine 100. The cooling flow 706 exits the impingement pocket 318 through the plurality of the cooling holes 324 arranged at the edges of the impingement pocket 318. The ring segment 202 with the pins 402 can be manufactured by conventional casting techniques, or by other techniques such as, by Selective Laser Melting (SLM) printing, or by Electrical Discharge Machining (EDM), etc.
The impingement plate 204 is fixedly connected to the ring segment 202 to cover the impingement pocket 318. The impingement plate 204 is welded around edges of the impingement pocket 318. The impingement plate 204 has a negative Poisson's Ratio structure that is provided by the bumps 602 and valleys 604. The negative Poisson's Ratio structure allows the impingement plate 204 to expand in two directions under a tension which reduces stress at the welding area. The fixed connection of the impingement plate 204 to the ring segment 202 reduces leakage of the cooling flow 706 in the impingement pocket 318 which improves cooling effect.
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.
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