• 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 method of machining a cast turbine blade (400) having a blade portion (402), a platform portion (406), and a root portion (408), the method comprising: machining an internal plenum in the turbine blade, the plenum having a plenum chamber (420 ), a plenum passage (428), and a plenum inlet (429) at the root portion (408) of the turbine blade.
    公开号:CH709943A2
    申请号:CH01016/15
    申请日:2015-07-13
    公开日:2016-01-29
    发明作者:Xiuzhang James Zhang；Lisa De Bellis；Haiping Wang
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Technical area
    The present invention relates to gas turbines. In particular, the invention relates to providing a cooling flow for cooling passages in turbine blades and for blade platforms.
    Background of the invention
    The turbine section of a gas turbine is exposed to high temperatures during operation. The rotating section of the turbine includes a series of wheels mounted on a shaft. The rim of the wheels includes an annular array of dovetail slots adapted to receive the dovetail portion of turbine blades. The turbine blades extend outwardly from the rim of the wheel into a hot gas passageway through the turbine. The blades on each wheel form a row of blades in the turbine. Hot combustion gases flowing through the hot gas passage apply aerodynamic forces to the blades which cause the blades, wheels and shaft to rotate to drive a compressor and an external device such as an electric generator.
    The turbine section includes rows of vanes secured to a stationary turbine housing. Each row of vanes extends inwardly from the housing into the hot gas passageway. Rows of vanes alternate with rows of blades. The vanes change direction and guide the gases flowing through the hot gas passage into each successive row of blades.
    The hot combustion gases can overheat and damage the turbine blades. To avoid overheating and heat damage, the blades are cooled by cooling gases flowing through internal passages in the blades.
    Referring to FIG. 1, a turbine blade 10 includes an airfoil 12, a shank portion 14, a platform 16, and a root portion 18. The turbine blades 10 are particularly susceptible to damage along the platform 16 of the blades 10.
    Turbine blade damage would cause a decline in gas turbine efficiency and would require replacement. Material costs for replacing a damaged blade are usually high and replacement of turbine blades would require failure of gas turbine operation. Therefore, the cost of operating a gas turbine would increase due to replacement material costs.
    It has been a constant search for improvements to solve turbine blade durability problems. Greater turbine blade life would require less blade replacement and lower the cost of running a turbine.
    Turbine blades are generally molded with a given number of air passages or cooling passages within the turbine blade. Different types of cooling passages are poured into the turbine blade depending on the cooling requirements.
    Many have tried to provide cooling for the paddle platforms. Cooling passages on the platforms are generally supplied with a cooling fluid, such as an airflow, obtained from an air passage that is poured into the root section, the airfoil section, or both root section and wing section.
    Attempts to solve the problem of turbine blade platform cooling have been described, for example, in U.S. Patent Nos. 8,641,368; 8,641,377; 2012/0082567; 7,416,391; 7309.212; 5,382,135; 2009/0202339; 6,416,284; and JP Patent Laid-Open Publication No. 2008202547.
    Brief description of the invention
    The present invention relates to methods and apparatus for adding or modifying cooling passages in cast turbine blades. The present invention provides adjustable plenum / adjustable plenums for distributing a cooling flow in a turbine blade to provide a cooling effect that counteracts the high ambient temperature. The adjustable plenums are machined into the cast turbine blades and can be used as new turbine blades or to upgrade and retrofit turbine blades that are currently in operation.
    An embodiment of a cast turbine blade having at least one machined plenum includes a turbine blade that has already been cast and into which at least one plenum is machined into the turbine blade. The plenum includes at least one plenum chamber, at least one plenum passage, and an inlet at the root portion of the turbine blade.
    [0013] In any embodiment of the invention, it may be advantageous if the at least one plenum is machined using a process that includes electrochemical machining tube forming (STEM), EDM, electrochemical machining, or a combination it is.
    In any embodiment of the invention, it may be advantageous if the plenum inlet to root portion is connected to a cooling flow source.
    In any embodiment of the invention, it may be advantageous if the turbine blade further comprises at least one cooling passage in the turbine blade.
    In any embodiment of the invention, it may be advantageous if the plenum is connected to the at least one cooling passage in the turbine blade.
    In any embodiment of the invention, it may be advantageous if the plenum has a shape that is rectangular, conical, cylindrical, hexagonal, curved, pyramidal or a combination thereof.
    In any embodiment of the invention, it may be advantageous if the plenum has more than one plenum passageway connected to a single plenum chamber.
    In any embodiment of the invention, it may be advantageous if the plenum has a plenum passageway connected to more than one plenum chamber.
    In any embodiment of the invention, it may be advantageous if the plenum does not coincide with at least one cast cooling channel within the turbine blade.
    In any embodiment of the invention, it may be advantageous if the plenum chamber is machined to have a horizontal dimension and a radial dimension, and the dimensions are greater than or equal to 1.2 times a diameter of the plenum passage.
    In any embodiment of the invention, it may be advantageous if the plenum passage does not have a uniform diameter over an entire length of the passage between the plenum chamber and the plenum inlet.
    In any embodiment of the invention, it may be advantageous if the plenum does not have a radial through-hole extending into the airfoil section.
    A method of supplying additional cooling flow to a cast turbine bucket includes machining at least one new plenum within a turbine bucket having at least one plenum chamber, at least one plenum passage, and an inlet to a root portion of the turbine bucket; connecting the turbine blade to a turbine wheel having a cooling flow source within the wheel; and diverting the cooling flow to enter the inlet of the plenum at the root portion of the turbine blade to the plenum chamber within the turbine blade.
    In any embodiment of the method, it may be advantageous if at least one cooling passage is provided within the turbine blade.
    In any embodiment of the method, it may be advantageous if at least one cooling passage is within a platform section of the turbine blade.
    In any embodiment of the method, it may be advantageous for the cooling flow to be routed to flow through the plenum passage, the plenum, and the at least one cooling passage.
    In any embodiment of the method, it may be advantageous if the at least one plenum is machined using a method that includes electrochemical machining tube forming (STEM), electroerosive machining (EDM), electrochemical machining, or a combination it is.
    In any embodiment of the method, it may be advantageous if the machining process includes removing material from within the turbine blade to make the plenum.
    Brief description of the drawings
    [0030]<Tb> FIG. 1 <SEP> is an illustration of a conventional turbine blade;<Tb> FIG. 2 <SEP> is a transparent view of an airfoil and a platform portion of a turbine blade illustrating conventionally cast cooling passages;<Tb> FIG. 3 <SEP> is a side view of an exemplary pair of turbine blades disposed on a turbine wheel showing an embodiment of the present invention;<Tb> FIG. Fig. 4 is a cross-sectional view of a turbine blade along a vertical axis of the turbine blade showing a second embodiment of the present invention;<Tb> FIG. Fig. 5 is a transparent view of an airfoil and platform portion of a turbine blade illustrating an embodiment with cooling passages; and<Tb> FIG. FIG. 6 is a transparent cross-sectional view taken along a surface of the platform facing the airfoil illustrating another embodiment with multiple plenums. FIG.
    Detailed description of the invention
    A conventional turbine bucket 10 is shown in FIG. 2, which generally includes an airfoil 15 disposed on a surface of the bucket platform 16, the turbine bucket 10 may include a main air passage 20 already cast in the bucket, such as through the airfoil 12, as shown. The main air channel 20 may be used to provide cooling liquid flow to the airfoil 12 and also to provide cooling flow for the cooling passages 24 in the platform. Other air channels 22 may also be poured into the blade 10 and may also provide cooling fluid for the cooling passages 24 or only for the airfoil 12.
    The cooling fluid flow may be diverted from the main air passage into which the connected cooling passages 24 and the cooling flow may exit through the holes 26 at the sides of the platform 16 or at the surface of the platform 16. The main air passage 20 may have a radial through hole extending into the airfoil portion 12 above the platform portion 16. The radial through hole would allow a cooling flow to enter the airfoil 12, as shown in FIG.
    However, the cast air passages 20, 22 may not be sufficient to promote cooling fluid flow to the desired locations on the turbine blade when dealing with the cooling requirements for a turbine blade due to improvements in the gas turbine or due to inaccuracies during casting of the turbine blade Change turbine blades.
    As is known in the art, a turbine blade is also known as a turbine blade. A turbine vane is also known as a turbine nozzle; a shaft portion is also known as a neck portion; and a root portion is also known as a dovetail of the turbine blade. These terms can be used interchangeably throughout the description. Corresponding parts on different embodiments are numbered the same.
    FIG. 3 provides a schematic view of two exemplary turbine blades 300 disposed on a wheel 330 in a gas turbine engine. On each wheel 330, the turbine blades 300 are juxtaposed to form an annular array of blades 300, which are a series of blades in the turbine. The turbine blades 300 may each be independently disposed on the wheel 330. The turbine blades include an airfoil section 302, a platform section 306, a shaft section 304, and a root section 308.
    The turbine blades 300 may be machined after casting to have one or more additional internal plenums within the blades 300. An internal plenum does not include radially extending passages in this context. One or more internal plenums may be machined to connect horizontal cooling passages and cooling holes disposed in the platform section 30 of the turbine blade 300.
    The internal plenums include internal plenum chambers 320 connected to root portion 308 through internal plenum passages 328. The internal plenum passages include inlets 329 at or radially inward of the rim of the wheel 330. The inlets 329 are open or otherwise in fluid communication with sources of cooling air 342, such as compressor air, which is directed by a gas turbine compressor to passages in the turbine that are radial are arranged inside of the hot gas passage. Cooling air 340 flows into the inlet 329 and through the internal plenum passages 328, through the internal plenum chambers 320, through any internal cooling passages in the platform 306 and the airfoil 302 of the blades, may then be discharged from these cooling passages, for example into the hot gas passage. The plenum chambers 320 and plenum passages 328 may also cool other portions of the turbine blade 300 as required or act as cooling passages themselves to provide cooling for desired parts of the turbine blade.
    The plenum chambers 320 and the plenum passages 328 may be formed by removing material from the blades 300 using any machining process including an electrochemical machining tubular molding process (STEM), an electrical discharge machining (EDM) process, an electrochemical machining process (US Pat. ECM) and a combination thereof.
    As an example, one embodiment is preferably set up using a STEM method to create a new plenum having a plenum chamber and a plenum passageway. A plenum may be machined in a turbine blade using the STEM process, by placing the turbine blade in an acidic solution, and by an electrolytic process that removes material from predetermined locations within the turbine blade.
    A source of cooling fluid flow 342, such as a rotor cooling circuit of the gas turbine, may supply cooling flow 340 for the turbine blades 300 from within or attached to the wheel 330 of a gas turbine engine. The cooling flow 340 may be diverted into the plenum passage 320 at the root portion 308 of the turbine blade 300 where a supply pressure of the cooling flow 340 in the gas turbine may be well defined. The inlet 329 to the plenum passage 328 may be provided at the apex of the root portion 308, along an outer periphery of the root portion 308, or otherwise suitably at the root portion 308.
    FIG. 4 provides a cross-sectional view of an exemplary turbine blade 400 showing a plenum with a plenum 420 connected to a root portion 408 of the turbine blade 400 using a plenum passage 428 having a plenum inlet 429 at the root portion 408. The plenum 420 is also connected to the cooling passage 424 in the platform 426.
    In one embodiment, the sizes of a plenum 420 and a plenum passage 428 are relatively fixed. A plenum 420 may have a horizontal dimension (D1) and a radial dimension (D2). Likewise, a plenum passage 428 may have a diameter (d) along a length (L) of the passage 428. The length (L) may be defined between the plenum 420 and the plenum inlet 429 in the turbine blade 400.
    The horizontal dimension (D1) of the plenum chamber 420 may be greater than or equal to 1.2 times the diameter (d) of the plenum passage 428 (eg, D1 ≥ 1.2 * d) and the radial dimension (D2) of the plenum chamber 420 may be greater than or equal to 1.2 times the diameter (d) of the plenum 428 (eg D2 ≥ 1.2 * d). In another embodiment, D1 and D2 of a plenum 420 may be unequal. The diameter (d) may be different over the entire length (L) of the plenum passage 428.
    Although only one cooling passage 424 is shown in FIG. 4, multiple cooling passages 424 may be in the turbine blade 400. The plenum 420 may provide a cooling flow 440 for one or more cooling passages 424 in the turbine blade 400, as shown in FIG. 5. A plenum 420 may supply a cooling flow 440 to more than one cooling passage 424 in the platform 406, and the cooling flow 440 may exit the passages 424 through cooling holes 426 at the end of the platform 406.
    In one embodiment, the plenum may not have a radial through-hole extending into the airfoil portion 402. Without a radial through hole extending from the plenum, as extending from plenum chamber 420, cooling flow 440 may be completely redirected into one or more cooling passages 424 connected to plenum 420.
    In another embodiment, cooling holes 426 may also be disposed on the surface of the platform 406 that faces the airfoil 402 to provide cooling flow to the airfoil 402. Likewise, cooling holes 426 may also be powered to provide film cooling to the platform 402. In addition, any arrangement of cooling channels 424 and cooling holes 426 may be supplied by plenum 420 and plenum passage 428.
    Referring to FIG. 6, more than one plenum 520 may be machined into the turbine blade 500. Each of the plenum chambers 520 may be used to guide a cooling flow 540 to more than one cooling passage 524. The plenum chambers 520 may be machined to any desired location in the turbine blade 500 that is suitable for supplying a cooling flow 540 to desired cooling passages 524 and locations on the blade 500.
    In addition, each plenum 520 may be connected to a single plenum passage or a plurality of plenum chambers 520 may be connected to a single plenum passage. The arrangement of plenum chambers 520 and plenum passageways may be determined as requirements occur and is not limited to any particular arrangement.
    In addition, the plenum chamber and the plenum passage may not be similarly shaped and may not be limited to a particular shape. The plenum and plenum passage may be machined to have a rectangular shape, a cylindrical shape, a conical shape, a pyramidal shape, a hexagonal shape, or any suitable shape or combination thereof. In addition, the plenum passage may also be curved. The plenum chamber and passage may also be present in different parts of the turbine blade for cooling purposes, such as in the stem, airfoil, platform and root sections.
    Advantages of machining additional plenums, which may or may not be consistent with the existing air channel in the cast turbine blade, include: providing additional cooling flow delivery for cooling passages as desired as turbine operation requirements change; Providing additional cooling flow delivery to newly proposed cooling passages as the turbine blades are improved; Improving defective turbine blades with misaligned air channels during casting; and providing additional cooling for the turbine blade using machined plenum passages and plenum chambers.
    While the invention has been described in conjunction with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiment, but on the contrary is intended to disclose various modifications and equivalents To include arrangements included within the spirit and scope of the appended claims.
    A cast turbine blade having at least one machined plenum containing a plenum chamber and at least one plenum passage connected to a plenum inlet at a root portion of the turbine blade, and a method for supplying a cooling flow to the turbine blade using the machined plenum, which receives the cooling flow from the root portion of the turbine blade.
    LIST OF REFERENCE NUMBERS
    [0053]<tb> 10 <SEP> conventional turbine blade<Tb> 12 <September> blade section<Tb> 14 <September> shaft section<Tb> 16 <September> platform section<Tb> 18 <September> root section<Tb> 20 <September> main air duct<tb> 22 <SEP> other air ducts<Tb> 24 <September> cooling passage<Tb> 26 <September> cooling hole<Tb> <September><tb> 300 <SEP> Turbine Blade (Embodiment FIG. 3)<Tb> 302 <September> blade section<Tb> 304 <September> shaft section<Tb> 306 <September> platform section<Tb> 308 <September> root section<Tb> 320 <September> plenum<Tb> 328 <September> Plenary passage<Tb> 329 <September> plenum inlet<Tb> 330 <Sept.> turbine<Tb> 340 <September> cooling flow<Tb> 342 <September> cooling flow source<Tb> <September><tb> 400 <SEP> Turbine Blade (Embodiment Figs. 4 and 5)<Tb> 402 <September> blade section<Tb> 404 <September> shaft section<Tb> 406 <September> platform section<Tb> 408 <September> root section<Tb> 420 <September> plenum<Tb> 424 <September> cooling passage<Tb> 426 <September> cooling hole<Tb> 428 <September> Plenary passage<Tb> 429 <September> plenum inlet<Tb> 440 <September> cooling flow<tb> (d) <SEP> Diameter of plenum passage<tb> (L) <SEP> Length of plenum passage<tb> (D1) <SEP> horizontal dimension of the plenum chamber<tb> (D2) <SEP> Radial dimension of the plenum chamber<Tb> <September><tb> 500 <SEP> Turbine Blade (Embodiment Fig. 6)<Tb> 502 <September> blade section<Tb> 506 <September> platform section<Tb> 520 <September> plenum<Tb> 524 <September> cooling passage<Tb> 526 <September> cooling hole<Tb> 540 <September> cooling flow
    权利要求:
    Claims (10)
    [1]
    A method of machining a cast turbine blade having an airfoil section, a platform section, and a root section, the method comprising:machining an internal plenum in the turbine blade, the plenum having a plenum chamber, a plenum passage, and a plenum inlet at the root portion of the turbine blade.
    [2]
    2. The method of claim 1, wherein the at least one plenum is machined using a method that is an electrochemical machining tube forming process (STEM), an electro-erosive machining process (EDM), an electrochemical machining process, or a combination thereof.
    [3]
    3. The method of claim 1 or 2, wherein the plenum inlet at the root portion is connected to a cooling flow source.
    [4]
    4. The method of claim 1, further comprising at least one cooling passage in the turbine bucket, the plenum being connected to the at least one cooling passage in the turbine bucket.
    [5]
    5. The method of claim 1, wherein the plenum has more than one plenum passage connected to a single plenum and / or wherein the plenum has a plenum passage connected to more than one plenum chamber.
    [6]
    6. The method of claim 1, wherein the plenum does not coincide with the at least one cast air channel within the turbine blade.
    [7]
    7. The method of claim 1, wherein the plenum chamber is machined to have a horizontal dimension and a radial dimension, and the dimensions are greater than or equal to 1.2 times a diameter of the plenum passage.
    [8]
    A method according to any one of the preceding claims, wherein the plenum passage does not have a uniform diameter throughout the entire length of the passage between the plenum chamber and the plenum inlet.
    [9]
    A method according to any one of the preceding claims, wherein the plenum has no radial through-hole extending into the airfoil section.
    [10]
    10. A method of delivering additional cooling flow to a cast turbine bucket, comprising: machining a plenum in a turbine bucket, the machining of the plenum forming a plenum chamber, a plenum passage and a plenum inlet in a root portion of the turbine bucket;Connecting the turbine blade to a turbine wheel; wherein the machining step comprises positioning an inlet to the plenum passage in the vicinity of a source of cooling air adapted to receive cooling air into the plenum, and redirecting the cooling flow to enter the inlet of the plenum at the root portion of the turbine blade to the plenum chamber to get inside the turbine blade.
    类似技术:
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    同族专利:
    公开号 | 公开日
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-03-29| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/335,047|US9708916B2|2014-07-18|2014-07-18|Turbine bucket plenum for cooling flows|
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