Patent Grant
11634996
This application claims priority to Korean Patent Application No. 10-2020-0038944, filed on Mar. 31, 2020, the disclosure of which is incorporated herein by reference in its entirety.
Apparatuses and methods consistent with exemplary embodiments relate to an apparatus for controlling turbine blade tip clearance and a gas turbine including the same.
Turbines are machines that obtain a rotational force by impingement or reaction force using a flow of a compressible fluid such as steam or gas, and include a steam turbine using steam, a gas turbine using hot combustion gas, and so on.
The gas turbine includes a compressor, a combustor, and turbine. The compressor has an air inlet for introduction of air thereinto, and includes a plurality of compressor vanes and a plurality of compressor blades alternately arranged in a compressor casing.
The combustor supplies fuel to air compressed by the compressor and ignites a mixture thereof with a burner to produce high-temperature and high-pressure combustion gas.
The turbine includes a plurality of turbine vanes and a plurality of turbine blades alternately arranged in a turbine casing. In addition, a rotor is disposed to pass through centers of the compressor, the combustor, the turbine, and an exhaust chamber.
The rotor is rotatably supported at both ends thereof by bearings. The rotor has a plurality of disks fixed thereto, and a plurality of blades are connected to each of the disks while a drive shaft of a generator is connected to an end of the exhaust chamber.
The gas turbine is advantageous in that consumption of lubricant is extremely low due to an absence of mutual friction parts such as a piston-cylinder because the gas turbine does not have a reciprocating mechanism such as a piston in a four-stroke engine. Therefore, an amplitude, which is a characteristic of reciprocating machines, is greatly reduced, and the gas turbine has an advantage of high-speed motion.
The operation of the gas turbine is briefly described. That is, the air compressed by the compressor is mixed with fuel for combustion to produce high-temperature and high-pressure combustion gas which is injected into the turbine, and the injected combustion gas generates a rotational force while passing through the turbine vanes and turbine blades, thereby rotating the rotor.
In this case, a gap defined as a tip clearance is formed between the turbine casing and each of the plurality of blades. If the tip clearance is increased above an acceptable level, an amount of combustion gas that is not activated and is discharged between the turbine casing and the blade, reducing an overall efficiency of the gas turbine. In contrast, if the tip clearance decreases below an appropriate level, the blade may scratch the inner wall of the turbine casing. Therefore, adjusting the tip clearance of the turbine to an appropriate level is closely related to improving the performance of the gas turbine.
Aspects of one or more exemplary embodiments provide an apparatus for controlling turbine blade tip clearance which allows a cooling plate to have an improved shape to supply cold air more efficiently, thereby enabling the cooling plate to contract further in a radial direction, and a gas turbine including the same.
Additional aspects will be set forth in part in the description which follows and, in part, will become apparent from the description, or may be learned by practice of the exemplary embodiments.
According to an aspect of an exemplary embodiment, there is provided an apparatus for controlling tip clearance between a turbine casing and a turbine blade, the apparatus including: a casing surrounding the turbine blade, a cooling plate installed in a groove and formed in a circumferential direction in the casing, the cooling plate being contracted by cold air supplied thereto, an upper plate mounted radially outside the cooling plate in the groove and having a plurality of cold air holes formed therein, a cylinder extending radially from an inner peripheral surface of the upper plate and having a plurality of cooling holes formed on a side thereof, and a ring segment mounted radially inside the cooling plate.
The plurality of cold air holes may include a first cold air hole for supplying cold air into the cylinder, and a plurality of second cold air holes arranged around the first cold air hole to supply cold air to a space between an outside of the cylinder and the inside of the cooling plate.
The plurality of second cold air holes may be obliquely formed to supply cold air toward an outer peripheral surface of the cylinder.
The cylinder may have a lower end integrally connected to an upper surface of the cooling plate.
The cooling plate may include a body disposed in the groove of the casing, a mounting groove formed radially inside the body, and a pair of side walls extending outward from both sides on a radially outer peripheral surface of the body.
The cylinder may include a plurality of cylinders arranged on the upper plate corresponding to one ring segment.
The plurality of second cooling holes may include four second cooling holes arranged at equal intervals around the first cooling hole.
The plurality of second cooling holes may include eight second cooling holes arranged around the first cooling hole.
Four of the plurality of second cooling holes may be arranged on different concentric circles around the first cooling hole, compared to the other four second cooling holes.
The plurality of cooling holes may be obliquely formed on a side wall of the cylinder.
According to an aspect of another exemplary embodiment, there is provided a gas turbine including: a compressor configured to compress outside air, a combustor configured to mix fuel with the air compressed by the compressor to burn a mixture thereof, a turbine including a plurality of turbine blades in a turbine casing rotated by combustion gas discharged from the combustor, and an apparatus for controlling tip clearance between the turbine casing and the turbine blade. The apparatus for controlling tip clearance may include a casing surrounding the turbine blade, a cooling plate installed in a groove and formed in a circumferential direction in the casing, the cooling plate being contracted by cold air supplied thereto, an upper plate mounted radially outside the cooling plate in the groove and having a plurality of cold air holes formed therein, a cylinder extending radially from an inner peripheral surface of the upper plate and having a plurality of cooling holes formed on a side thereof, and a ring segment mounted radially inside the cooling plate.
The plurality of cold air holes may include a first cold air hole for supplying cold air into the cylinder, and a plurality of second cold air holes arranged around the first cold air hole to supply cold air to a space between an outside of the cylinder and the inside of the cooling plate.
The plurality of second cold air holes may be obliquely formed to supply cold air toward an outer peripheral surface of the cylinder.
The cylinder may have a lower end integrally connected to an upper surface of the cooling plate.
The cooling plate may include a body disposed in the groove of the casing, a mounting groove formed radially inside the body, and a pair of side walls extending outward from both sides on a radially outer peripheral surface of the body.
The cylinder may include a plurality of cylinders arranged on the upper plate corresponding to one ring segment.
The plurality of second cooling holes may include four second cooling holes arranged at equal intervals around the first cooling hole.
The plurality of second cooling holes may include eight second cooling holes arranged around the first cooling hole.
Four of the plurality of second cooling holes may be arranged on different concentric circles around the first cooling hole, compared to the other four second cooling holes.
The plurality of cooling holes may be obliquely formed on a side wall of the cylinder.
The above and other aspects will become more apparent from the following description of the exemplary embodiments with reference to the accompanying drawings, in which:
Various modifications and various embodiments will be described below in detail with reference to the accompanying drawings so that those skilled in the art can easily carry out the disclosure. It should be understood, however, that the various embodiments are not for limiting the scope of the disclosure to the specific embodiment, but they should be interpreted to include all modifications, equivalents, and alternatives of the embodiments included within the spirit and scope disclosed herein.
The terminology used herein is for the purpose of describing specific embodiments only and is not intended to limit the scope of the disclosure. The singular expressions “a”, “an”, and “the” are intended to include the plural expressions as well unless the context clearly indicates otherwise. In the disclosure, terms such as “comprises”, “includes”, or “have/has” should be construed as designating that there are such features, integers, steps, operations, components, parts, and/or combinations thereof, not to exclude the presence or possibility of adding of one or more of other features, integers, steps, operations, components, parts, and/or combinations thereof.
Further, terms such as “first,” “second,” and so on may be used to describe a variety of elements, but the elements should not be limited by these terms. The terms are used simply to distinguish one element from other elements. The use of such ordinal numbers should not be construed as limiting the meaning of the term. For example, the components associated with such an ordinal number should not be limited in the order of use, placement order, or the like. If necessary, each ordinal number may be used interchangeably.
Hereinafter, a tip clearance control apparatus and a gas turbine including the same according to exemplary embodiments will be described with reference to the accompanying drawings. It should be noted that like reference numerals refer to like parts throughout the specification. In certain embodiments, a detailed description of functions and configurations well known in the art may be omitted to avoid obscuring appreciation of the disclosure by a person of ordinary skill in the art. For the same reason, some components may be exaggerated, omitted, or schematically illustrated in the accompanying drawings.
Referring to
The air compressed by the compressor 1100 flows to the combustor 1200. The combustor 1200 includes a plurality of combustion chambers 1210 and fuel nozzle modules 1220 arranged annularly.
Referring to
Based on the direction of an air flow, the compressor 1100 is disposed at an upstream side, and the turbine 1300 is disposed at a downstream side. A torque tube 1500 serving as a torque transmission member for transmitting the rotational torque generated in the turbine 1300 to the compressor 1100 is disposed between the compressor 1100 and the turbine 1300.
The compressor 1100 includes a plurality of compressor rotor disks 1120, each of which is fastened by a tie rod 1600 to prevent axial separation in an axial direction of the tie rod 1600.
For example, the compressor rotor disks 1120 are axially aligned in a state in which the tie rod 1600 forming a rotary shaft passes through the centers of the compressor rotor disks 1120. Here, adjacent compressor rotor disks 1120 are arranged so that facing surfaces thereof are in tight contact with each other by being pressed by the tie rod 1600. The adjacent compressor rotor disks 1120 cannot rotate because of this arrangement.
Each of the compressor rotor disks 1120 has a plurality of blades 1110 radially coupled to an outer peripheral surface thereof. Each of the blades 1110 has a dovetail 1112 fastened to the compressor rotor disk 1120.
A plurality of vanes are fixedly arranged between each of the compressor rotor disks 1120 in the housing 1010. While the compressor rotor disks 1120 rotate along with a rotation of the tie rod 1600, the vanes fixed to the housing 1010 do not rotate. The vanes guide the flow of the compressed air moved from front-stage blades 1110 to rear-stage blades 1100.
The dovetail 1112 may be fastened by a tangential type or an axial type, which may be selected according to a structure of a gas turbine. The dovetail 1112 may have a dovetail shape or a fir-tree shape. In some cases, the blades 1110 may be fastened to the compressor rotor disks 1120 by using other types of fastening members such as a key or a bolt.
The tie rod 1600 is disposed to pass through centers of the plurality of compressor rotor disks 1120 and turbine rotor disks 1322. The tie rod 1600 may be a single tie rod or a plurality of tie rods. One end of the tie rod 1600 is fastened to a most upstream compressor rotor disk, and the other end thereof is fastened by a fixing nut 1450.
It is understood that the type of the tie rod 1600 may not be limited to the example illustrated in
Also, in order to increase the pressure of fluid and adjust an actual inflow angle of the fluid entering into an inlet of the combustor, a deswirler serving as a guide vane may be installed at the rear stage of the diffuser of the compressor 1100 so that the actual inflow angle matches a designed inflow angle.
The combustor 1200 mixes fuel with the introduced compressed air, burns a fuel-air mixture to produce high-temperature and high-pressure combustion gas with high energy, and increases the temperature of the combustion gas to a temperature at which the combustor and the turbine components are able to be resistant to heat through an isobaric combustion process.
A plurality of combustors constituting the combustor 1200 may be arranged in the housing in a form of a cell. Each of the combustors may include a burner having a fuel injection nozzle and the like, a combustor liner defining a combustion chamber, and a transition piece serving as a connection between the combustor and the turbine.
The combustor liner provides a combustion space in which the fuel injected by the fuel injection nozzle is mixed with the compressed air supplied from the compressor. The combustor liner may include a flame container providing the combustion space in which the mixture of air and fuel is burned, and a flow sleeve defining an annular space while surrounding the flame container. The fuel injection nozzle is coupled to a front end of the combustor liner, and an ignition plug is coupled to a side wall of the combustor liner.
The transition piece is connected to a rear end of the combustor liner to transfer the combustion gas toward the turbine. An outer wall of the transition piece is cooled by the compressed air supplied from the compressor to prevent the transition piece from being damaged due to the high temperature of the combustion gas.
To this end, the transition piece has cooling holes through which the compressed air is injected, and the compressed air cools the inside of the transition piece and then flows toward the combustor liner.
The compressed air that has cooled the transition piece may flow into an annular space of the combustor liner, and may be supplied as a cooling air through the cooling holes formed in the flow sleeve from the outside of the flow sleeve to an outer wall of the combustor liner.
The high-temperature and high-pressure combustion gas ejected from the combustor 1200 is supplied to the turbine 1300. The supplied high-temperature and high-pressure combustion gas expands and applies impingement or reaction force to the turbine blades to generate rotational torque. A portion of the obtained rotational torque is transmitted via the torque tube to the compressor, and the remaining portion which is the excessive torque is used to drive a generator or the like.
The turbine 1300 basically has a structure similar to the compressor 1100. That is, the turbine 1300 includes a turbine rotor 1320 similar to the rotor of the compressor 1100. The turbine rotor 1320 includes a plurality of turbine rotor disks 1322 and a plurality of turbine blades 1324 arranged radially. The turbine blades 1324 may be coupled to the turbine rotor disk 1322 in a dovetail coupling manner or the like.
In addition, a plurality of turbine vanes 1314 fixed to a turbine casing 1312 are provided between the turbine blades 1324 of the turbine rotor disk 1322 to guide a flow direction of the combustion gas passing through the turbine blades 1324. In this case, the turbine casing 1312 and the turbine vanes 1314 corresponding to a fixing body may be collectively referred to as a turbine stator 1310 in order to distinguish them from the turbine rotor 1320 corresponding to a rotating body.
Referring to
Referring back to
The branch passage 1800 may be formed outside the compressor casing or may be formed inside the compressor casing by passing through the compressor rotor disk 1120. The branch passage 1800 may supply the compressed air branched from the compressor 1100 to the turbine rotor disk 1322. The compressed air supplied to the turbine rotor disk 1322 flows radially outward, and may be supplied to the turbine blade 1324 to cool the turbine blade 1324. In addition, the branch passage 1800 connected to the outside of the housing 1010 may supply the compressed air branched from the compressor 1100 to the turbine casing 1312 to cool the inside of the turbine casing 1312. The branch passage 1800 may be provided with a valve 1820 in a middle thereof to selectively supply compressed air. The branch passage 1800 may be connected to a heat exchanger to selectively further cool the compressed air prior to supply.
Referring to
The casing 110 is a turbine casing disposed to be spaced apart from the ends of a plurality of turbine blades 1324 by a predetermined distance. The groove may be formed in a circumferential direction at a position in which each ring segment 150 is mounted in the casing 110.
The cooling plate 120 may be installed in the groove of the casing 110, and may be formed of a plurality of segments arranged in the circumferential direction.
The ring segment 150 may be mounted in a mounting structure provided radially inside the cooling plate 120. The ring segment 150 may include a body 152 in a form of a plate bent in a circumferential direction, and a mounting rib portion 154 extending outward from the radially outer surface of the body 152 and then extending axially outward.
The cooling plate 120 may include a body 122 disposed in the groove of the casing 110, a mounting groove 124 formed radially inside the body 122, and a pair of side walls 125 extending outwardly from both sides on the radially outer peripheral surface of the body 122.
The body 122 may be in a form of an arc-shaped plate segment bent in the circumferential direction.
The mounting groove 124 is formed radially inside the body 122. The mounting groove 124 may form a groove for inserting the mounting rib portion 154 of the ring segment 150, in a manner that extends radially inward from both axial edges of the inner peripheral surface and bends so that inner ends thereof face each other.
The pair of side walls 125 may be in a form of a rib extending outwardly from both edges on the radially outer peripheral surface of the body 122. As described above, the mounting rib 126 may or may not be formed on the axially outside the upper end of each side wall 125.
Here, the pair of side walls 125 are referred to as side walls because they extend from the edge of the body 122 and are in contact with the inner surface of the groove of the casing 110. However, the side walls 125 may be in the form of a rib such as a fin to serve as a cooling fin to which cold air is supplied.
The upper plate 130 is mounted radially outside the cooling plate 120 in the groove of the casing 110. The cooling plate 120 may be in a form of an arc-shaped plate segment bent in the circumferential direction. The plurality of cold air holes 132 and 134 may be formed radially through the cooling plate 120 at a portion to which the cylinder 140 is connected and a portion around the cylinder 140.
The cylinder 140 may be formed integrally by extending radially to the inner peripheral surface of the upper plate 130. The cylinder 140 may be in a form of a circular pipe with a closed lower end. The plurality of cooling holes 142 may be formed on a lower side of the cylinder 140. The lower end of the cylinder 140 comes into contact with the body 122 of the cooling plate 120.
The plurality of cold air holes formed in the upper plate 130 may include a first cold air hole 132 for supplying cold air to the cylinder 140, and a plurality of second cold air holes 134 arranged around the first cold air hole 132 to supply cold air to a space between the outside of the cylinder 140 and the inside of the cooling plate 120.
As illustrated in
The plurality of second cooling holes 134 may include four or more second cooling holes formed around the first cooling hole 132. The plurality of second cooling holes 134 may be arranged such that an imaginary concentric circle connecting centers of the second cooling holes 134 is larger than an outer diameter of the cylinder 140.
The plurality of second cooling holes 134 may be obliquely formed to supply cool air toward the outer peripheral surface of the cylinder 140. The lower end of the cylinder 140 is in contact with the cooling plate 120. Therefore, when the cylinder 140 is cooled, the cold air may be delivered to the cooling plate 120 by conduction. To this end, the cold air supplied from the radially outer side of the upper plate 130 may intensively cool the cylinder 140 through the plurality of second cooling air holes 134.
It is preferable that the lower end of the cylinder 140 is integrally connected to an upper surface of the body 122 of the cooling plate 120. Here, the upper surface of the body 122 is based on
Referring to
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Accordingly, the tip clearance control apparatus can control the amount of radial deformation of the cooling plate such that the cooling plate is displaced at a minimum of about 0.32 mm and a maximum of about 0.43 mm depending on whether cold air is supplied.
Referring to
Referring to
Accordingly, the tip clearance control apparatus can control the amount of radial deformation of the cooling plate such that the cooling plate is displaced at a minimum of about 0.56 mm and a maximum of about 0.69 mm depending on whether cold air is supplied. It can be seen that when more cylinders are arranged in this way, the cooling plate moves radially over a wider range than when providing one cylinder.
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When the gas turbine starts to operate, the turbine blade 1324 heats up rapidly. Accordingly, the tip clearance between the ring segment 150 and the turbine blade 1324 becomes small. Therefore, at the time of starting, heated air is supplied to the cooling plate 120 to move the ring segment 150 radially outward, thereby preventing the end of the turbine blade 1324 from contacting the ring segment 150.
Because the tip clearance increases under normal conditions when the gas turbine is operated at a constant rotational speed, cold air is supplied to the cooling plate 120 to move the ring segment 150 radially inward, thereby keeping the tip clearance small at an appropriate interval.
As described above, according to the apparatus for controlling turbine blade tip clearance and the gas turbine including the same, because the shape of the cooling plate has been improved to supply cold air more efficiently, the cooling plate can contract further in the radial direction.
Accordingly, the ring segment mounted on the cooling plate can move further in the radial direction, and the turbine blade tip clearance can be adjusted over a wider range.
While one or more exemplary embodiments have been described with reference to the accompanying drawings, it will be apparent to those skilled in the art that various variations and modifications in form and details may be made by adding, changing, or removing components without departing from the spirit and scope of the disclosure as defined in the appended claims, and these variations and modifications fall within the spirit and scope of the disclosure as defined in the appended claims. Accordingly, the description of the exemplary embodiments should be construed in a descriptive sense only and not to limit the scope of the claims, and many alternatives, modifications, and variations will be apparent to those skilled in the art.
| Number | Date | Country | Kind |
|---|---|---|---|
| 10-2020-0038944 | Mar 2020 | KR | national |
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| 2788590 | Oct 2014 | EP |
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| Entry |
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| KR OA dated Apr. 28, 2021. |
| Number | Date | Country | |
|---|---|---|---|
| 20210301674 A1 | Sep 2021 | US |
