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 turbine vanes often operate in a high temperature environment and are internally cooled.
In one aspect, a turbine blade includes a platform defining a first side and a second side. The turbine blade also includes a blade airfoil attached to the first side of the platform, the blade airfoil includes a pressure side wall and a suction side wall defining a blade airfoil interior. The turbine blade also includes a blade root attached to the second side of the platform, the blade root including a blade root leading edge and a blade root trailing edge with respect to a flow direction of a working flow, the blade root defining a first cooling passage and a second cooling passage that are in flow communication with the blade airfoil interior. The turbine blade also includes a manifold attached to the blade root, the manifold being non-planar, the manifold includes an outer wall, a first compartment having a first flow area defined by a first aperture, the first aperture being formed at the outer wall and open to the first compartment, the first compartment metering a non-zero first flow of cooling air to the first cooling passage through the first flow area, and a second compartment having a second flow area defined by a second aperture, the second aperture being formed at the outer wall and open to the second compartment, the second compartment metering a non-zero second flow of cooling air to the second cooling passage through the second flow area that is different than the first flow area.
In one aspect, a manifold for use with a turbine blade, the manifold includes a first side plate, a second side plate, an outer plate that extends between the first side plate and the second side plate, a forward plate attached to the first side plate, the second side plate, and the outer plate at one end, an aft plate attached to the first side plate, the second side plate, and the outer plate at the other side that is opposite to the one end, a first compartment having a first flow area defined by a first aperture, the first aperture being formed at the first side plate and open to the first compartment, a second compartment having a second flow area defined by a second aperture, the second aperture being formed at the first side plate and open to the second compartment, the second flow area being different than the first flow area.
In one aspect, a manifold for use with a turbine blade, the manifold includes a first compartment having a first compartment outer wall, the first compartment outer wall defining a first aperture that is open to the first compartment, the first aperture defining a first flow area, and a second compartment having a second compartment outer wall, the second compartment outer wall defining a second aperture that is open to the second compartment, the second aperture defining a second flow area that is different than the first flow area.
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 turbine blade 200 includes a platform 202, a blade airfoil 204, and a blade root 206. The platform 202 has a first side 208 that faces away from the rotor 134 and a second side 210 that is opposite to the first side 208 and faces toward the rotor 134.
The blade airfoil 204 is attached to the platform 202 at the first side 208. The blade airfoil 204 has a pressure side wall 212 and a suction side wall 214. The pressure side wall 212 and the suction side wall 214 meet at a blade airfoil leading edge 216 and a blade airfoil trailing edge 218 with respect to a flow direction of a working flow 234. The working flow 234 may be the exhaust gas 122 from the combustion section 104. The pressure side wall 212 and the suction side wall 214 define a blade airfoil interior 220.
The blade root 206 is attached to the platform 202 at the second side 210. The blade root 206 has a blade root leading edge 236 and a blade root trailing edge 238 with respect to the flow direction of the working flow 234. The blade root 206 includes a plurality of cooling passages that are defined within the blade root 206. In the construction illustrated in
The turbine blade 200 includes a manifold 300 that is attached to the blade root 206 at a side facing to the rotor 134. The manifold 300 is non-planar and meters or controls the quantity of cooling air that flows to each cooling passage of the plurality of cooling passages or blocks the cooling air from entering at least one of the cooling passages.
The manifold 300 includes a plurality of divider plates 312 that divide the manifold 300 into a plurality of compartments. Each divider plate 312 of the plurality of divider plates 312 is solid and perpendicular to the outer plate 306. In the construction illustrated in
The first side plate 302 and the second side plate 304 define a plurality of apertures 326. In the construction shown in
In the construction shown in
In other constructions, each compartment may have different numbers of apertures 326 than the manifold 300 shown in
The forward plate 308 has a general square shape having rounded edges. The forward plate 308 is perpendicularly welded or brazed to the first side plate 302, second side plate 304, and the outer plate 306.
The aft plate 310 has a general square shape having rounded edges. The aft plate 310 is perpendicularly welded or brazed to the first side plate 302, second side plate 304, and the outer plate 306. The aft plate 310 is thicker than the forward plate 308. In other constructions, the aft plate 310 may be thinner or equal to the forward plate 308.
Each divider plate 312 has a general square shape having rounded edges. Each divider plates 312 has a cutout 404 to engage with the outer plate 306. Each divider plate 312 is inserted into one of the gaps 402 and welded or brazed to the first side plate 302, the second side plate 304, and the outer plate 306.
In the construction shown in
In the construction shown in
IG. 8 illustrates a perspective view of a manifold 800 suitable for use with the turbine blade 200 shown in
In the construction shown in
Each of the compartments has a compartment outer wall 804. The compartment outer wall 804 may have a compartment outer plate 806 that is spaced a non-zero distance away from the base plate 802. Apertures 326 are defined at the compartment outer wall 804. As illustrated in
In other constructions, the first leading compartment 314, the second leading compartment 316, and the first mid compartment 318 may have at least one aperture 326 that is formed at the compartment outer wall 804 of the respective first leading compartment 314, the second leading compartment 316, and the first mid compartment 318. It is also possible that the second mid compartment 320, the first trailing compartment 322, and the second trailing compartment 324 are solid. It is also possible that the apertures 326 are formed at the compartment outer plate 806.
The manifold 900 has a plurality of base plates. The plurality of base plates are separated pieces from each other. Each of the first leading compartment 314, the second leading compartment 316, the first mid compartment 318, the second mid compartment 320, the first trailing compartment 322, and the second trailing compartment 324 is formed at one of the plurality of base plates and extends out from the respective base plate.
For example, in the construction shown in
The first leading compartment 314 is formed at the first base plate 902 and extends out from the first base plate 902. The second leading compartment 316 is formed at the second base plate 904 and extends out from the second base plate 904. The first mid compartment 318 is formed at the third base plate 906 and extends out from the third base plate 906. The first leading compartment 314 has at least one aperture 326 that is formed at the compartment outer wall 804 of the first leading compartment 314. The second leading compartment 316 has at least one aperture 326 that is formed at the compartment outer wall 804 of the second leading compartment 316. The first mid compartment 318 has at least one aperture 326 that is formed at the compartment outer wall 804 of the first mid compartment 318.
Further compartments, such as the second mid compartment 320, the first trailing compartment 322, and the second trailing compartment 324 may be each formed at a further base plate. It is possible that at least one of the compartment outer walls 804 is solid.
In the construction shown in
The manifold 800 may be replaced by the manifold 900 to be attached to the blade root 206. Each separated base plate is attached to the blade root 206 and the compartment that is formed at the base plate is inserted into one of the cooling passages. For example, the first base plate 902 is attached to the blade root 206 and the first leading compartment 314 that is formed at the first base plate 902 is inserted into the first leading cooling passage 222. The second base plate 904 is attached to the blade root 206 and the second leading compartment 316 that is formed at the first base plate 902 is inserted into the second leading cooling passage 224. The third base plate 906 is attached to the blade root 206 and the first mid compartment 318 that is formed at the third base plate 906 is inserted into the first mid cooling passage 226. Further base plates may be attached to the blade root 206 and further compartments each formed at one of the further base plates may be inserted into one of the second mid cooling passage 228, the first trailing cooling passage 230, and the second trailing cooling passage 232.
In other constructions, the manifold 800 and manifold 900 may be attached to the blade root 206 in a way such that the compartments extend out a non-zero distance away from the cooling passages, respectively.
In operation, with reference to
The cooling air 704 enters the manifold 300, or the manifold 500 from the first side plate 302 and the second side plate 304 which generate effective mixing before entering the cooling passages. The cooling air 704 turns 90 degrees in the compartments and flows into the cooling passages to reduce the cooling air 704 bias from the downstream side to the upstream side.
The first leading compartment 314 meters a non-zero first flow of cooling air 704 to the first leading cooling passage 222 through the flow area of the apertures 326 in the first leading compartment 314. The second leading compartment 316 meters a non-zero second flow of cooling air 704 to the second leading cooling passage 224 through the flow area of the apertures 326 in the second leading compartment 316. The first mid compartment 318 meters a non-zero third flow of cooling air 704 to the first mid cooling passage 226 through the flow area of the apertures 326 in the first mid compartment 318. The second mid compartment 320 meters a non-zero fourth flow of cooling air 704 to the second mid cooling passage 228 through the flow area of the apertures 326 in the second mid compartment 320. The first trailing compartment 322 has no apertures 326 so that the cooling air 704 is blocked from entering the first trailing cooling passage 230. The second trailing compartment 324 meters a non-zero fifth flow of cooling air 704 to the second trailing cooling passage 232 through the apertures 326 in the second trailing compartment 324. The non-zero first flow of cooling air 704, the non-zero second flow of cooling air 704, the non-zero third flow of cooling air 704, the non-zero fourth flow of cooling air 704, and the non-zero fifth flow of cooling air 704r may be different from each other.
Discrete throttling control (i.e., by selecting aperture flow areas) of the flow of cooling air 704 that flows to each cooling passage is achieved by different arrangements of the compartments. In general, the flow areas of the apertures 326 in the compartments at the blade root leading edge 236 is larger than the flow areas of the apertures 326 in the compartments at the blade root trailing edge 238. For example, in manifold 300 and manifold 500, the flow area of the apertures 326 in the second leading compartment 316 and the flow area of the apertures 326 in the first mid compartment 318 is larger than the flow area of the apertures 326 in the first leading compartment 314, the flow area of the apertures 326 in the second mid compartment 320, and the flow area of the apertures 326 in the second trailing compartment 324. As such, the cooling air 704 is the least throttled in the second leading compartment 316 and the first mid compartment 318 than in the first leading compartment 314, the second mid compartment 320, and the second trailing compartment 324. The first trailing compartment 322 has no apertures 326 such that the cooling air 704 is blocked from entering the first trailing cooling passage 230.
The manifolds better controls the cooling air 704 flowing into the cooling passages which allows more accurate prediction for the life of the blade. In addition, the manifolds assist in reducing leakages of the cooling air 704.
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.
Number | Date | Country | |
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63359501 | Jul 2022 | US |