• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A turbine rotor blade includes platform cooling means (130) connected to a platform (110), the rotor blade having an inner cooling channel, and wherein in operation the inner cooling channel includes a high pressure coolant section and a low pressure coolant section and wherein the platform (110) extends in a direction an axis of rotation of the turbine rotor blade facing platform underside (114). The platform cooling assembly (130) includes: a first plate (132) spaced from the platform bottom (114) and forming a first cavity (133); a second plate (138) spaced from the first plate (132), the second plate (138) defining a second cavity (139). The second cavity (139) includes an inlet channel (141) connected to the high pressure coolant portion of the inner cooling channel, and the second cavity (133) includes an outlet channel (142) connected to the low pressure cooling portion of the inner cooling channel. The first plate (132) has a number of baffles (140), and the first plate (132), the second plate (138) and the platform (110) are separately formed components.
    公开号:CH703875B1
    申请号:CH01589/11
    申请日:2011-09-27
    公开日:2016-01-15
    发明作者:Scott Edmond Ellis；John Wesley Harris Jr；Adrian Lional Scott
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to a platform cooling arrangement for a turbine rotor blade, in particular for use in gas turbines, which, unless otherwise specified otherwise, includes all types of gas turbines, such as those used for power generation, as well as those of aircraft.
    A gas turbine typically includes a compressor, a burner and a turbine. The compressor and turbine generally include rows of blades or blades arranged axially in steps one behind the other. Each stage typically includes a series of circumferentially spaced rotor blades that are fixedly disposed and a set of circumferentially spaced rotor blades that rotate about a central axis or shaft. In operation, the rotor blades of the compressor are rotated about the shaft to compress an airflow. The compressed air is then used in the burner to burn supplied fuel. The hot gas stream resulting from the combustion process is then expanded as it passes through the turbine causing the rotor blades to rotate the shaft to which they are attached. In this way, the energy contained in the fuel is converted into the mechanical energy of the rotating shaft, which can then be used for example to drive generator coils to generate electricity.
    Reference is made to FIGS. 1 and 2; The rotor blades 100 of the turbine generally include a blade section or blade 102 and a root section or root 104. The blade 102 has a convex suction surface 105 and a concave pressure surface 106. The blade 102 also has a leading edge 107 which is the leading edge and a trailing edge 108 which is the trailing edge. The foot 104 has a structure (which typically includes a dovetail 109, as shown) for securing the blade 100 to the rotor shaft, a platform 110 from which the blade 102 extends away, and a shank 112 which defines the structure between the shaft Dovetail 109 and the platform 110 includes.
    As shown, the platform 110 may be substantially planar. Specifically, the platform 110 may have a planar top surface 113 which, as illustrated in FIG. 1, has an axially and circumferentially extending flat surface. As illustrated in FIG. 2, the platform 110 may include a flat bottom 114 that also has an axially and circumferentially extending flat surface. The top 113 and the bottom 114 of the platform 110 may be formed to be oriented substantially parallel to one another. As illustrated, it can be seen that the platform 110 typically has a thin radial profile, that is, there is a relatively small radial distance between the top 113 and the bottom 114 of the platform 110.
    Generally, the platform 110 on a turbine rotor blade 100 is used to form the inner flow path boundary of the hot gas path portion of the gas turbine. The platform 110 also provides structural support to the blade 102. In operation, the rotational speed of the turbine causes a mechanical stress that creates high stress areas along the platform 110 such that, in conjunction with high temperatures, operational failures may eventually occur, such as oxidation, creep , Fatigue fractures at low load cycles and the like. Of course, these defects negatively impact the useful life of the rotor blade 100. It can be seen that these harsh operating conditions, i. exposure to high temperatures of the hot gas path and mechanical loading applied to the rotating blades, creates a significant challenge in designing durable, durable rotor blade platforms 110 that perform well as well as cost effectively.
    A common solution to make platform section 110 more durable is to cool it during operation with a flow of compressed air or other coolant, a variety of such designs being known. However, those skilled in the art will understand that the platform portion 110 poses a certain design challenge that makes it difficult to cool it in this manner. Much of this is due to the awkward geometry of this region due to platform 110 being a peripheral component located away from the central core of the rotor blade and typically arranged thereon, of structurally sound but radially small thickness to have.
    For supplying the coolant, the rotor blade 100 typically has one or more cooling channels 116 (see Figs. 3, 4 and 5) extending radially at least through the core of the blade 100 including the foot 104 and the blade 102. As will be described in more detail below, such cooling channels 116 may be formed to increase heat exchange in the form of serpentines winding through the central portions of the blade 100, although other configurations are possible. During operation, coolant may flow into the central cooling channels via one or more inlets 117 formed in the inlet portion of the foot 104. The coolant may circulate through the blade 100 and exit through outlets (not shown) formed on the blade and / or through one or more outlets (not shown) formed in the foot 104. The coolant may be under pressure such as compressed air, compressed air mixed with water, steam or the like. In many cases, the refrigerant is compressed air that has been tapped from the compressor of the gas turbine, although other sources are possible. As described in more detail below, the cooling channels typically include a high pressure cooling region and a low pressure cooling region. The high-pressure cooling zone typically corresponds to an upstream section of the cooling channel, which has a higher coolant pressure, whereas the low-pressure cooling zone corresponds to a downstream section, in which a comparatively lower coolant pressure prevails.
    In some cases, the coolant may be directed out of the cooling channels 116 into a cavity 119 formed between the shafts 112 and platforms 110 of adjacent rotor blades 100. From there, the coolant may be used to cool the platform portion 110 of the blade, a conventional design of which is illustrated in FIG. In this design, air is typically extracted from one of the cooling channels 116, and the air is used to pressurize the cavity 119 formed between the shafts 112 and platforms 110, respectively. Once pressurized, the cavity 119 then delivers coolant to cooling channels that extend through the platforms 110. After traversing the platform 110, the cooling air may exit the cavity through film cooling holes formed in the top surface 113 of the platform 110.
    However, it is understood that this type of conventional design has several disadvantages. First, the cooling circuit is not completely formed in one part, because the cooling circuit is formed only after two adjacent rotor blades 100 are assembled. This leads to high demands and complexity in terms of installation and flow tests before installation. A second disadvantage is that the integrity of the cavity 119 formed between adjacent rotor blades 100 depends on how well the periphery of the cavity 119 is sealed. A poor seal can mean insufficient platform cooling and / or cooling air loss. A third disadvantage is the inherent risk that hot gas path gases will be sucked into the cavity 119 or the platform 110 itself. This can be done if the cavity 119 is not maintained at a sufficiently high pressure during operation. When the pressure in the cavity 119 drops below the pressure prevailing in the hot gas path, hot gases enter the stem cavity 119 or the platform 110 itself, which typically damages these components, because they are not designed to be permanently exposed to the conditions in the hot gas path ,
    Figures 4 and 5 illustrate another type of conventional platform cooling design. In this case, the refrigeration cycle is included in the rotor blade 100 and, as shown, does not include a stem cavity 119. Cooling air is removed from one of the cooling channels 116 extending through the core of the blade 110 and through cooling channels 120 formed in the platform 110 are formed (ie, "platform cooling channels 120"), directed backwards. As indicated by various arrows, the cooling air flows through the platform cooling channels 120 and exits through outlets in the trailing edge 121 of the platform 110 or outlets formed along the suction edge 122. (It is noted that in describing or referring to edges or surfaces of the rectangular platform 110, any may be described based on their arrangement with respect to the suction surface 105 or pressure surface 106 of the sheet 102 and / or the forward and aft direction of the gas turbine, As far as the bucket 100 is installed, the platform can, as one skilled in the art will appreciate, have a trailing edge 121, a suction side edge 122, a leading edge 124, and a pressure side edge 126, as indicated in Figures 3 and 4. In addition, the suction side edge 122 can and the pressure-side edge 126 may be referred to as "impact surfaces", wherein the cavity formed between them when adjacent rotor blades 100 are installed may be referred to as a "shock cavity".)
    It will be appreciated that the conventional structures of Figs. 4 and 5 have an advantage over the structure of Fig. 3 in that they are not affected by variations in assembly or installation conditions. However, conventional designs of this type have various limitations and disadvantages. First, as shown, only one circuit is provided on each side of the blade 102, and thus there is the disadvantage of limited control of the amount of cooling air used at various locations on the platform 110. Second, conventional designs of this type have a coverage area that is generally limited. While the serpentine tortuous path of FIG. 5 is an improvement over the cover of FIG. 4, dead zones still exist in the platform 110 which remain uncooled. Third, manufacturing costs dramatically increase when, to achieve better coverage with internally formed platform cooling channels 120, the cooling channels have particular shapes requiring a molding process to form them. Fourth, these conventional designs typically discharge coolant after use and before full utilization of the coolant in the hot gas path, adversely affecting the efficiency of the gas turbine. Fifth, designs of this kind generally have little flexibility. This means that the channels 120 are formed as an integral part of the platform 110 and leave little or no opportunity to change their function or configuration as operating conditions vary. Moreover, these types of conventional designs are difficult to repair or repair.
    As a result, conventional platform cooling structures have disadvantages in one or more areas. The object on which the present invention is based, therefore, is to provide a platform cooling arrangement and a method for its production, which ensures effective and efficient cooling of the platform area of turbine rotor blades, which is cost-effective to produce and flexible in use and durable.
    Brief description of the invention
    The present invention thus describes a turbine rotor blade with a platform cooling assembly connected to a platform which, in the installed state of the turbine rotor blade in the turbine with respect to a rotational axis of the turbine rotor blade at a radial height at a connection between a blade and a foot the rotor blade having a cooling passage formed therein extending from a port of a coolant source at the root to at least about the radial position of the platform, the cooling passage having in operation a high pressure coolant region and a low pressure coolant region, and wherein the platform along its inner surface has a platform underside. The platform cooling assembly includes: a first plate spaced inside and to the platform bottom, the first plate being formed to define a first volume between the first plate and the platform bottom; and a second plate disposed inside and spaced from the first plate, the second plate configured to define a second volume between the second plate and the first plate. The second volume has a first inlet channel that connects to the high pressure coolant area of the inner cooling channel. The first volume has at least one outlet channel that connects to the low pressure coolant region of the inner cooling channel. The first plate has a number of impact openings. The first plate, the second plate and the platform are separately formed components.
    The present invention also relates to a method for producing a turbine rotor blade with platform cooling arrangement according to the invention, comprising the following steps:Manufacturing the exhaust passage having a predetermined configuration and arrangement such that it connects the low pressure coolant portion of the inner cooling passage to the first cavity once the first cavity is formed;Manufacturing the inlet duct, which has a predetermined configuration and arrangement such that it connects the high-pressure coolant section of the inner cooling channel with the second cavity as soon as the second cavity is formed;Attaching the first plate to the turbine rotor blade; andAttach the second plate to the first plate.
    These and other features of the present invention will become apparent from the following detailed description of the preferred embodiments when taken in conjunction with the drawings and the following claims.
    Brief description of the drawings
    These and other features of the invention will be more fully understood and appreciated by a careful study of the following more particular description of exemplary embodiments of the invention, taken in conjunction with the accompanying drawings, in which:<Tb> FIG. 1 <SEP> illustrates a perspective view of an exemplary turbine rotor blade in which embodiments of the present invention may be utilized;<Tb> FIG. Figure 2 illustrates a bottom view of a turbine rotor blade in which embodiments of the present invention may be used;<Tb> FIG. FIG. 3 illustrates a cross-sectional view of adjacent turbine rotor blades having a cooling system according to a conventional construction; FIG.<Tb> FIG. FIG. 4 illustrates a plan view of a turbine rotor blade having a platform with internal cooling channels according to a conventional construction; FIG.<Tb> FIG. 5 illustrates a plan view of a turbine rotor blade having a platform with internal cooling channels according to an alternative conventional design;<Tb> FIG. FIG. 6 illustrates a cross-sectional side view of a platform cooling arrangement according to one embodiment of the present application; FIG.<Tb> FIG. Fig. 7 is a perspective view of a first plate and a second plate according to an embodiment of the present invention;<Tb> FIG. Fig. 8 is a cross-sectional plan view of a platform cooling arrangement according to an embodiment of the present application; and<Tb> FIG. 9 is a flowchart illustrating an exemplary method of creating the platform cooling arrangement according to one embodiment of the present application.
    Detailed description of the invention
    It is understood that turbine blades cooled by the internal circulation of a coolant typically have an internal cooling channel 116 extending radially outwardly from the foot through the platform portion and into the blade portion, as described above with respect to various conventional cooling structures is described. It should be understood that certain embodiments of the present invention may be utilized in conjunction with conventional cooling channels to enhance or facilitate efficient active platform cooling, with the present invention being discussed in conjunction with a conventional configuration, namely, an inner cooling channel 116, that winds or runs as a serpentine. As illustrated in FIGS. 6, 8, and 9, the serpentine path is typically configured to permit unidirectional coolant flow and contain structural details that promote heat exchange between the coolant and the surrounding rotor blade 100. During operation, a pressurized refrigerant, which is typically compressed air bled from a compressor (other types of refrigerant, such as steam, may be utilized in various embodiments of the present invention), may be passed through a passageway 104 through the foot 104 the interior of the cooling channel 116 passed. The pressure drives the coolant through the inner cooling passage 116 and the coolant absorbs heat from the surrounding walls.
    As can be readily appreciated, as the coolant passes through the cooling passage 116, the coolant loses pressure so that the coolant in the upstream portions of the internal cooling passage 116 has a higher pressure than the coolant in downstream portions. As discussed in greater detail below, this pressure differential may be used to propel the coolant over or through cooling channels formed in the platform. It will be appreciated that the present invention may be used with rotor blades 100 having internal cooling channels of different configurations and not limited to serpentine internal cooling channels. Accordingly, as used herein, the term "inner cooling channel" or "cooling channel" includes any passage or channel through which coolant can be directed within the rotor blade. As anticipated herein, the internal cooling passage 160 of the present invention extends at least approximately to the radial position of the platform 116 and may include at least a portion of comparatively higher coolant pressure (hereinafter referred to as the "high pressure section", which in some instances is an upstream section within one Serpentine channels) and at least a portion of relatively lower refrigerant pressure (hereinafter referred to as "low pressure section" and which may be a downstream region relative to the high pressure section within a serpentine channel).
    In general, the various configurations of conventional internal cooling channels 116 are effective in providing active cooling for particular areas within the rotor blade 100. However, as the person skilled in the art knows, the platform areas prove to be more difficult. This is at least partially due to the difficult platform geometry, i. its small radial height and the way in which it is away from the core or main body of the rotor blade 100. Given the high temperatures to which it is exposed in the hot gas path and the high mechanical stress, the cooling requirements of the platform are quite considerable. As described above, conventional platform cooling designs are ineffective because they do not address the specific challenges of this area, are inefficient in terms of refrigerant utilization, and costly to manufacture.
    Reference is again made to Figs. 6 to 9, which illustrate various views of exemplary embodiments of the present invention. FIG. 6 illustrates a cross-sectional side view of a platform cooling assembly 130 according to an embodiment of the present invention, while FIG. 8 shows a cross-sectional top view thereof. 7 illustrates a perspective view of a first plate 132 (which may be referred to as an "outer plate" or "baffle plate") and a second plate 138 (which may be referred to as an "inner plate" or "closure plate") according to an embodiment of the present invention , As illustrated, a platform 110 may be disposed at the junction between the blade 102 and the root 104 of the rotor blade 100.
    The platform 110 may include a platform bottom 114 along an inboard surface of the platform 110. Like the top 113 of the platform, the bottom 114 may have an axially and circumferentially extending planar surface. (Note that "planar" as used herein means approximately or substantially in the form of a plane.) For example, it will be appreciated by those skilled in the art that platforms may have an outboard surface that is slightly curved or convex, with the curvature corresponding to the perimeter of the As used herein, this type of platform shape is considered planar because the radius of curvature is sufficiently large to give the platform a flat appearance.) In one embodiment of the present invention, in Platform bottom 114 may be formed a flat pocket 131. The flat bag 131 may be formed by one or more manufacturing methods such as, but not limited to, machining, casting, or the like. For example, an existing rotor blade may be machined to form a corresponding flat pocket 131. In one embodiment of the present invention, the flat pocket 131 may be disposed at a portion of the platform bottom 114 that substantially coincides with the pressure side of the blade 102 of the blade. In another embodiment of the present invention, the flat pocket 131 may be configured to receive at least two stacked panels to form a platform cooling assembly as described herein.
    Fig. 6 illustrates a sectional view of a platform cooling assembly 130 according to an exemplary embodiment of the present invention. The platform cooling assembly 130 may include a first baffle plate 132 disposed inboardly spaced relation to the platform bottom 114 so as to form a first volume 133, also referred to as a first cavity, between the baffle plate 132 and the platform bottom 114. A second or end plate 138 may be located inboard spaced from the baffle plate 132 such that a second volume 139, also referred to as a second cavity, is formed between the end plate 138 and the baffle plate 132. In one embodiment of the present invention, the baffle plate 132 and / or the end plate 138 may be substantially planar. In addition, the baffle plate 132 and the end plate 138 may be disposed in a portion of the platform lower surface 114 that substantially coincides with the pressure side of the sheet 102.
    In one embodiment of the present invention, the baffle plate 132 may have many baffles 140 that may extend through the thickness of the baffle plate 132. The baffles 140 may be configured so that when compressed air is introduced into the second volume 139, the baffles 140 will cause the pressurized refrigerant to discharge and thus create coolant jets that strike and cool the platform lower surface 114. The baffles 140 may have a free cross-sectional flow area of a predetermined size, so that a desired Kühlmittelauftreffcharakteristik is achieved, assuming further operating conditions, such as increasing the speed at which a coolant flow hits a target surface. Generally, it will be appreciated that the cooling effect when the coolant flow is directed against an impact surface is improved with a resulting high velocity coolant flow. The impact openings 140 can also have a cross-sectional area of a predetermined size, so that a desired coolant flow characteristic is achieved taking into account further operating criteria. As used herein, the term "intake characteristic" refers to a desired coolant distribution (or expected coolant distribution) across the impingement ports 140. The impingement ports 140 may be configured to direct a flow of coolant substantially toward the platform bottom 114. It will be appreciated that such impingement cooling can improve the cooling of the platform 110. In one embodiment of the present invention, the baffle openings 140 may have a substantially cylindrical shape. However, other forms of baffle openings may be used, such as, but not limited to, cubic, prismatic or other shapes. In addition, other diameter sizes are possible. Further, the baffles 140 may be oriented substantially perpendicular to the surface of the baffle plate 132. The baffles 140 may also be oriented obliquely with respect to the surface of the baffle plate 132.
    In one embodiment of the present invention, the second volume may include at least one inlet or inlet channel (which may be referred to as high pressure connector 141) in fluid communication with the high pressure portion of the inner cooling channel 116. The first volume 133 may include at least one outlet or outlet channel (which may be referred to as low pressure connector 142) in fluid communication with the low pressure coolant portion of the inner cooling channel 116. In various embodiments of the present invention, the high pressure connector 141 and / or the low pressure connector 142 may be formed by one or more methods such as, but not limited to, abrading, casting, or the like. In operation, the coolant flowing through the high pressure coolant portion of the inner cooling passage 116 may reach the second volume 139 via the high pressure connector 141. Thereafter, the coolant may flow through the baffles 140 and provide the baffle cooling of the platform 110 by impacting the platform lower surface 114. Subsequently, the coolant may exit the first volume 133 via the low pressure connector 142 to the low pressure coolant portion of the inner cooling channel 116. As noted, due to the above-described functional relationship between various components of the platform cooling assembly 130, the first plate 132 may be described as a "baffle plate" or "outboard plate", and the second plate 138 may be referred to as an "end plate" or "inboard board". In addition, the first volume 133 and the second volume 139 may be referred to as post-impact volume and corresponding pre-impact coolant volume.
    In one embodiment of the present invention, the baffle plate 132 may include a raised portion 144 which may serve as a spacer or stop so as to define a radial height of the first volume 133. The raised portion 144 of the baffle plate 132 may have a substantially constant height such that there is a predetermined distance between the baffle plate 132 and the platform bottom 114. The predetermined distance may provide a desired configuration of the first volume 133 and may be based on a distance at which the impingement cooling of the platform bottom 114 has a desired impingement cooling or heat transfer characteristic. In another embodiment of the present invention, the raised portion 144 of the baffle 132 may form an outer edge lip that extends around the perimeter of the baffle 132. The outer lip of the baffle plate 132 may be configured to form a seal on the platform bottom 114 during assembly. This may seal the first volume 133 at its periphery and substantially prevent coolant leakage from the first volume 133.
    In one embodiment of the present invention, the end plate 138 may also include a raised portion 146. The raised portion 146 of the end plate 138 may have a substantially constant height such that upon assembly there is a certain or desired distance between the baffle plate 132 and the end plate 138. The predetermined distance may provide a desired configuration of the second volume 139. In another embodiment of the present invention, the raised portion 136 of the end plate 138 may include an outer edge lip that extends along the perimeter of the end plate 138. The outer edge lip or edge of the end plate 138 may be configured to form a seal against the baffle plate 132 after assembly. Thus, the second volume 139 may be sealed along the periphery of the second volume 139 and coolant leakage from the second volume 139 may be substantially prevented. In addition, the sealing of the first volume 133 and the second volume 139 may substantially form a closed loop between the inlet channel 141 and the outlet channel 142. Thus, coolant flowing through the first volume 133 and the second volume 139 may return to the inner cooling passage 116 for further use. Those skilled in the art will understand that any other type of sealant may be used between the baffle plate 132 and the platform bottom 114 and between the baffle plate 132 and the end plate 138, such as, but not limited to, a mechanical seal, a chemical sealant, or the like.
    In one embodiment of the present invention, the baffle plate 132 and the end plate 138 are not integrally formed components. In another embodiment of the present invention, the baffle plate 132, the end plate 138, and the platform 110 may each be non-integral components. In another embodiment of the present invention, the baffle plate 132 and the end plate 138 may be integral components, and the integrally formed first plate and second plate may be non-integral components with respect to the platform 110. In various embodiments of the present invention, the baffle plate 132 and / or the end plate 138 may be securely joined to the platform 110 by one or more methods, such as, but not limited to, welding, brazing, gluing, and the like. However, because the plates 132, 138 are not integrally formed with the platform 110 of the rotor blade 100, each part remains removable (ie, it can be removed for refurbishment, repair, reconciliation, and / or re-attached for continued use or other similar or modified components), assuming some kind of the above-mentioned conventional compounds.
    Although not shown, in some embodiments, film cooling holes may be formed through the outer walls defining the first volume 133 and the second volume 139. These may be used to allow a coolant to enter the cavity defined by the abutting surfaces of adjacent rotor blades 100.
    Those skilled in the art will recognize that the platform cooling assembly 130 may be retrofitted to existing turbine rotor blades in which at least one of the first and second plates 132 and 138 and the platform 110 are non-integral components. In addition, the platform cooling assembly 130 may utilize existing internal cooling passages 116 of turbine rotor blades, which provides the flexibility to utilize embodiments of the present invention with existing vanes or new blades. The baffle plate 132 and the end plate 138 may also be adjustable by changes made after casting. Various impact parameters, including, but not limited to, the number, dimensions and location of the baffles 140 and the exact profile of the first and second plates 132, 138 may be changed to optimize impact cooling of the platform 110. Thus, the platform cooling assembly 130 may be tailored to suit various turbine blade configurations and / or changing conditions.
    The platform cooling assembly 130 may also rely on a cost effective and efficient manufacturing process by separately manufacturing the first plate 132 and the second plate 138 from various components of the turbine rotor blades. In addition, the first and second panels 132 and 138 may be prefabricated and then assembled on site.
    Fig. 7 illustrates views of the baffle plate 132 and the end plate 138 according to an exemplary embodiment of the present invention. In one embodiment of the present invention, the baffle plate 132 may include a curved edge 154 and a straight edge 155. In another embodiment of the present invention, the curved edge 154 may approximate the shape of the curved profile of the blade 102. In another embodiment of the present invention, the end plate 138 may have substantially the same profile as the baffle plate 132, and may include a curved edge 158 and a straight edge 159. This may allow the end plate 138 to be aligned substantially below the baffle plate 132 to form the second volume 139. In addition, the flat pocket 131 may have a profile shape that substantially matches the profile of the baffle plate 132.
    As further illustrated in FIG. 7, the baffle openings 140 of the baffle plate 132 could be arranged substantially in many rows. The rows of baffle openings 140 may be substantially perpendicular or oblique to the straight edge 155 of the baffle plate 132. However, the baffles 140 may be arranged in any other configuration (e.g., stepped) without departing from the scope of the present application. In one embodiment of the present invention, the baffle plate 132 may include a central raised portion 164. The central raised portion 164 of the baffle plate 132 may enhance the impingement cooling of the platform 110 by dividing the first volume 133 into two sections. In another embodiment of the present invention, the end plate 138 may also include a central raised portion 166. The central raised portion 166 may affect the flow of coolant from the second volume 139 through the baffles 140.
    FIG. 9 illustrates a flowchart 200 illustrating an exemplary method of creating a platform cooling arrangement 130 according to an embodiment of the present invention. The flowchart 200 may begin at a step 202 in which the exhaust port or low pressure connector 142 is being machined. The exhaust passage 142 may have a predetermined configuration and arrangement such that the exhaust passage 142 connects the low-pressure coolant portion of the inner cooling passage 116 to the first volume 133 once the first volume 133 is formed. Subsequently, the inlet port or high pressure connector 141 may be processed in step 204. The intake passage 141 may have a predetermined configuration and arrangement such that the intake passage 141 connects the high-pressure coolant portion of the inner cooling passage 116 to the second volume 139 once the second volume 139 is formed.
    In a step 206, the flat pocket 131 may be formed in the platform lower side 114 at a position substantially coincident with the pressure side of the sheet 102. In addition, the flat pocket 131 may have a profile shape that substantially matches the profile of the printed side of the sheet and the profile of the baffle plate 132 and the end plate 138.
    In a step 207, the baffle plate 132 and the end plate 138 may be manufactured according to desired specifications.
    In a step 208, the baffle plate 132 may be connected to the platform lower side 114 so that the baffle plate 132 is fixed inside and at a distance from the platform lower side 114, so that the first volume 133 between the baffle plate 132 and the platform bottom 114 is formed becomes. In addition, the baffle plate 132 may be connected to the platform bottom 114 so that the baffle plate 132 is disposed within the flat pocket 131. Subsequently, the end plate 138 may be secured to the baffle plate 132 in a step 210 such that the end plate 138 is disposed inside and spaced from the baffle plate 132 such that the second volume 139 is defined between the baffle plate 132 and the end plate 138. In addition, the end plate 138 may be connected to the baffle plate 132 so that the profiles of the baffle plate 132 and the end plate 138 are substantially aligned with each other.
    In a step 212, the first volume 133 may be sealed along an interface between the outer edge lip 314, the baffle plate 132, and the platform bottom 114. Thereafter, the second volume 139 may be sealed in a step 214 along an interface between the outer edge lip of the end plate 138 and the baffle plate 132. The sealing of the first volume 133 and the second volume 139 may result in a substantially closed flow path between the inlet channel and the outlet channel.
    In a turbine rotor blade 100, a platform cooling device 130 can be arranged on a platform 110, wherein the rotor blade 100 has an inner cooling channel 116 and wherein in operation the inner cooling channel 116 has a high-pressure coolant section and a low-pressure coolant section and wherein the platform 110 has an axis of rotation the turbine rotor blade facing platform bottom 114 has. The platform cooling assembly 130 includes: a first plate 132 spaced from the platform bottom 114 and forming a first cavity 133; a second plate 138 spaced from the first plate 132, the second plate 138 defining a second cavity 139. The second cavity 139 includes an inlet channel 141 connected to the high pressure coolant section of the inner cooling channel 116, and the second volume 133 includes an outlet channel 142 connecting to the low pressure cooling section of the inner cooling channel 116.
    LIST OF REFERENCE NUMBERS
    [0039]<Tb> 100 <September> turbine rotor blade<Tb> 102 <September> Sheet<Tb> 104 <September> foot<Tb> 105 <September> suction<Tb> 106 <September> print area<Tb> 107 <September> leading edge<Tb> 108 <September> trailing edge<Tb> 109 <September> Swallowtail<Tb> 110 <September> Platform<Tb> 112 <September> End<Tb> 113 <September> Platform top<Tb> 114 <September> Platform base<tb> 116 <SEP> inner cooling channel<Tb> 117 <September> inlet<Tb> 119 <September> cavity<Tb> 120 <September> platform cooling channels<Tb> 121 <September> trailing edge<tb> 122 <SEP> Suction side edge or impact surface<Tb> 124 <September> leading edge<tb> 126 <SEP> Print side edge or impact surface<Tb> 130 <September> platform cooling arrangement<tb> 131 <SEP> flat bag<tb> 132 <SEP> first plate (flapper)<tb> 133 <SEP> first cavity, also referred to as first volume (external volume or post-impact volume)<tb> 138 <SEP> second plate (end plate)<tb> 139 <SEP> second cavity, also referred to as second volume (inboard volume or pre-impact volume)<Tb> 140 <September> impingement holes<tb> 141 <SEP> High Pressure Connector (Intake Channel)<tb> 142 <SEP> Low Pressure Connector (Outlet Channel)<tb> 144 <SEP> raised section of the first plate<tb> 146 <SEP> raised section of the second plate<tb> 154 <SEP> curved edge of the first plate<tb> 155 <SEP> straight edge of the first plate<tb> 158 <SEP> curved edge of the second plate<tb> 159 <SEP> straight edge of the second plate<tb> 164 <SEP> central raised portion of the first plate<tb> 166 <SEP> central raised portion of the second plate
    权利要求:
    Claims (10)
    [1]
    A turbine rotor blade (100) having a platform cooling arrangement (130),wherein the platform cooling assembly (130) is connected to a platform (110) which, when installed, the turbine rotor blade in the turbine with respect to a rotational axis of the turbine rotor blade at a radial height at a connection between a blade (102) and a foot (104). the turbine rotor blade (100), the turbine rotor blade (100) having an inner cooling channel (116) formed therein extending from connection to a source of coolant at the foot (104) substantially to the radial height of the platform (110). wherein the inner cooling channel (116) has a high-pressure coolant section and a low-pressure coolant section in operation, and wherein the platform (110) has a platform lower side (114) pointing in the direction of the rotational axis,wherein the platform cooling assembly (130) comprises: a first panel (132) spaced from the platform underside (114), the first panel (132) being configured to extend between the first panel (132) and the platform bottom (114) ) a first cavity (133) is formed;a second plate (138) spaced from the first plate (132), the second plate (138) being formed to define a second cavity (139) between the second plate (138) and the first plate (132) ), wherein:the second cavity (139) has at least one inlet channel (141) connected to the high pressure coolant portion of the inner cooling channel (116);the first cavity (133) has at least one outlet channel (142) connected to the low pressure coolant portion of the inner cooling channel (116);the first plate (132) has a number of baffles (140); andthe first plate (132), the second plate (138) and the platform (110) are separately formed components.
    [2]
    The turbine rotor blade (100) of claim 1, wherein the first plate (132) and the second plate (138) are releasably connected to the platform (110).
    [3]
    A turbine rotor blade (100) according to claim 1, wherein:the platform bottom (114) of the platform (110) is planar;the inner cooling channel (116) is serpentine; in use, a coolant having a coolant flow direction flows through the inner cooling passage (116); and the high-pressure coolant portion includes, with respect to the coolant flow direction, an upstream portion of the inner cooling passage (116) and the low-pressure coolant portion includes a downstream portion of the inner cooling passage (116).
    [4]
    4. The turbine rotor blade (100) of claim 1, wherein the platform bottom (114) is planar with respect to the axis of rotation in the axial and circumferential directions;the first plate (132) has a planar plate and on one side of the planar plate has a raised portion (144) configured to define a predetermined distance between the first plate (132) and the platform bottom (114);the second plate (138) comprises a planar plate and on one side of the planar plate has a raised portion (146) adapted to maintain a predetermined distance between the second plate (138) and the first plate;the raised portion (144) of the first plate (132) has an outer edge lip;the outer edge lip of the first plate (132) extends along the circumference of the first plate (132);the outer edge lip of the first plate (132) is configured to form a seal on the platform lower surface (114) and thereby seal the first cavity (133) along its circumference;the raised portion (146) of the second plate (138) has an outer edge lip;the outer edge lip of the second plate (138) extends along the circumference of the second plate (138); andthe outer edge lip of the second plate (138) is adapted to form a seal against the first plate (132) and thus to seal the second cavity (139) along its circumference.
    [5]
    The turbine rotor blade (100) of claim 1, wherein the baffles (140) include holes extending through the thickness of the first plate (132) such that upon supply of pressurized refrigerant to the second cavity (139), the baffles (140) expel pressurized refrigerant; andwherein the baffles (140) are configured to direct a flowing flow of coolant against the platform underside (114).
    [6]
    A turbine rotor blade (100) according to claim 1, wherein:the first plate (132) is a baffle plate;the second plate (138) is an end plate;the outlet passage (142) of the first cavity (133) connects the low pressure coolant portion of the inner cooling passage (116) via a manufactured low pressure connector (142) which, in use, recombines coolant after impact with the flow of coolant through the inner cooling passage (116);the inlet channel (141) of the second cavity (139) connects the high pressure coolant portion of the inner cooling passage (116) via a generated high pressure connector (141) through which, prior to impact, coolant is discharged from the inner cooling passage (116) and to the second cavity (14); 139) is guided; andthe first cavity (133) and the second cavity (139) are sealed such that substantially all of the flowing coolant flow is returned to the inner cooling channel (116).
    [7]
    A method of making a turbine rotor blade (100) having a platform cooling assembly (130) according to claim 1, said method comprising the steps of:Manufacturing the exhaust passage (142) having a predetermined configuration and arrangement so as to connect the low-pressure coolant portion of the inner cooling passage (116) with the first cavity (133) once the first cavity (133) is formed;Manufacturing the inlet duct (141) having a predetermined configuration and arrangement such that it connects the high-pressure coolant section of the inner cooling duct (116) with the second cavity (139) as soon as the second cavity (139) is formedAttaching the first plate (132) to the turbine rotor blade (100); andAttaching the second plate (138) to the first plate (132).
    [8]
    8. The method of claim 7, wherein:the first plate (132) has an outer edge lip extending continuously along the circumference of the first plate (132), the outer edge lip of the first plate (132) having a predetermined height that is substantially constant; andthe second plate (138) having an outer edge lip extending continuously along the circumference of the second plate (138), the outer edge lip of the second plate (138) having a predetermined height that is substantially constant;further having the steps that:the first cavity (133) is sealed along the interface between the outer edge lip of the first plate (132) and the platform bottom (114); and sealing the second cavity (139) along the interface between the outer edge lip of the second plate (138) and the first plate (132);wherein the sealing of the first cavity (133) and the second cavity (139) provides a closed flow path between the high pressure connector (141) and the low pressure connector (142).
    [9]
    The method of claim 7, wherein the first panel (132) has a profile with a curved edge (154) and a straight edge (155), the curved edge (154) substantially conforming to the shape of the curved profile of the blade (15). 102) coincides at the location where the sheet (102) is connected to the platform (110);further comprising the step of forming a pocket (131) in the platform underside (114) at a location coincident with the pressure side (106) of the sheet (102), the pocket (131) having a profile shape conforming to the profile of the sheet first plate (132) matches;wherein the first plate (132) is connected to the platform bottom (114) so that the first plate (113) is located in the pocket (131).
    [10]
    The method of claim 9, wherein the second plate (138) has substantially the same profile as the first plate (132), and wherein the second plate (138) is connected to the first plate (132) so that the profiles the first plate (132) and the second plate (138) are substantially aligned.
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    同族专利:
    公开号 | 公开日
    DE102011053891A1|2012-04-05|
    US8840369B2|2014-09-23|
    CN102444432A|2012-05-09|
    CH703875A2|2012-03-30|
    US20120082548A1|2012-04-05|
    JP5898900B2|2016-04-06|
    CN102444432B|2015-06-17|
    JP2012077747A|2012-04-19|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-04-30| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/894,934|US8840369B2|2010-09-30|2010-09-30|Apparatus and methods for cooling platform regions of turbine rotor blades|
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