US20070212228A1 - Moving blade for a turbomachine, the blade having a common cooling air feed cavity - Google Patents
Moving blade for a turbomachine, the blade having a common cooling air feed cavity Download PDFInfo
- Publication number
- US20070212228A1 US20070212228A1 US11/682,517 US68251707A US2007212228A1 US 20070212228 A1 US20070212228 A1 US 20070212228A1 US 68251707 A US68251707 A US 68251707A US 2007212228 A1 US2007212228 A1 US 2007212228A1
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- US
- United States
- Prior art keywords
- blade
- cavity
- root
- common cavity
- turbomachine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 38
- 206010042674 Swelling Diseases 0.000 claims abstract description 15
- 230000008961 swelling Effects 0.000 claims abstract description 15
- 238000011144 upstream manufacturing Methods 0.000 claims description 10
- 239000003351 stiffener Substances 0.000 claims description 3
- 238000005266 casting Methods 0.000 description 6
- 239000000919 ceramic Substances 0.000 description 5
- 239000002184 metal Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005219 brazing Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
Definitions
- the present invention relates to the general field of cooling moving blades in a turbomachine, and in particular the moving blades of the high-pressure turbine.
- a main object of the present invention is thus to mitigate such drawbacks by providing a moving blade provided with internal cooling circuits that are simpler to fabricate by casting and in which the flow of air is facilitated.
- the process of fabricating such a blade by casting is simplified.
- the ceramic core is consolidated by the presence of the location reserved for the common cavity for feeding air to the cavities of the cooling circuit(s).
- the presence of such a common cavity in the blade root avoids curving the cavities of the cooling circuit(s), thereby improving the flow of air therein.
- the presence of the common cavity makes it possible to make blades having a large cross-section—and thus an enlarged root—without thereby significantly increasing their weight (the purpose of using blades having a large cross-section is to reduce the total number of the moving blades in a given stage of a gas turbine).
- the common cavity has keying means for ensuring that a plate for calibrating the flow rates of air fed to the cavities of the cooling circuit(s) cannot be installed the wrong way round.
- the common cavity may be open in part through an upstream wall so as to facilitate feeding air to said common cavity.
- the end wall of the common cavity may be inclined from upstream to downstream relative to the base of the blade root in such a manner as to facilitate feeding air to said common cavity.
- Said common cavity may include a radial wall forming a stiffener disposed so as to subdivide the cavity into at least two sub-cavities.
- the invention also provides a turbomachine, and a high-pressure turbine for a turbomachine, each including a plurality of moving blades as defined above.
- FIG. 1 is a longitudinal section view of a moving blade of the invention
- FIGS. 2A and 2B are fragmentary perspective views of the root of the FIG. 1 blade.
- FIGS. 3A and 3B are fragmentary section views of moving blades constituting other embodiments of the invention.
- FIGS. 1 , 2 A, and 2 B show a moving blade 10 for a turbomachine, such as a moving blade of a high-pressure turbine.
- a turbomachine such as a moving blade of a high-pressure turbine.
- the invention can also be applied to other moving blades of the turbomachine, for example to the low-pressure turbine blades thereof.
- the blade 10 has an aerodynamic surface that extends radially between the blade root 12 and a blade tip 14 .
- This aerodynamic surface comprises a leading edge 16 placed facing the flow of hot gas coming from the combustion chamber of the turbomachine, a trailing edge 18 opposite to the leading edge 16 , a pressure side face, and a suction side face, the side faces (not shown in the figures) interconnecting the leading edge 16 and the trailing edge 18 .
- the blade 10 also has two lower swellings (or teeth) 12 a disposed laterally on either side of the blade root 12 and two upper swellings 12 b also disposed laterally on either side of the root, these swellings 12 a , 12 b defining bearing surfaces for fastening the root in a slot in a rotor disk (not shown).
- the section of the blade root defined between the lower and upper swellings 12 a and 12 b is referred to as a lower neck 12 c
- the section defined between the upper swellings 12 b and the bottom face of the platform 12 e of the root is referred to as an upper neck 12 d.
- the blade 10 has at least one internal cooling circuit.
- This circuit comprises one or more cavities 20 extending radially over the full height of the blade, one or more air admission openings 22 formed in the blade root 12 and leading to the cavity(ies) 20 , and a plurality of outlet orifices 24 opening out from the cavity(ies) and leading to the outside of the blade.
- FIG. 1 there are four internal cooling circuits for the blade 10 : one circuit situated in the vicinity of the leading edge 16 of the blade and formed by two radial cavities 20 a that are fed from an air admission opening 22 a ; two circuits situated in the central portion of the blade, one of them being formed by three radial cavities 20 b that are fed by an air admission opening 22 b , and the other being formed of two radial cavities 20 c that are fed by an air admission opening 22 c ; and a circuit situated in the vicinity of the trailing edge 18 of the blade and formed by a radial cavity 20 d which is fed by an air admission opening 22 d.
- All of the cooling circuits are also provided with outlet orifices, respectively referenced 24 a to 24 d , that open out from the radial cavities 20 a to 20 d and lead to the outside of the blade.
- outlet orifices respectively referenced 24 a to 24 d , that open out from the radial cavities 20 a to 20 d and lead to the outside of the blade.
- the blade 10 is typically obtained by casting a metal in a mold containing a ceramic core that has the function of occupying the positions of the radial cavities 20 or of the internal cooling circuits of the blade
- the air admission openings 22 of the internal cooling circuit(s) of the blade 10 all open out into a common cavity 26 formed in the blade root 12 .
- the common cavity 26 may present a shape that is substantially in the form of a rectangular parallelepiped, as shown in FIGS. 1 , 2 A, and 2 B.
- a common cavity may present a section area of about 2000 square millimeters (mm 2 ), the cavities of the cooling circuit(s) generally having sections of about 4 mm 2 to 30 mm 2 .
- the common cavity 26 extends radially from the base 12 f of the blade root 12 at least as far as the upper swellings 12 b thereof. This disposition makes it possible to obtain a cavity that is “tall”, thereby limiting head losses in feeding the cooling cavities 20 a to 20 d . In addition, the feed of cooling air to the cavities is more uniform.
- the common cavity 26 has keying means 28 to ensure that a plate 30 for calibrating the flow rates of air feeding the cavities 20 or the internal cooling circuit(s) of the blade can be fitted in a correct orientation only.
- a plate 30 for calibrating the flow rates of air feeding the cavities or the internal cooling circuit(s) of a blade is well known in itself. Typically, it is constituted by a metal plate 30 that is secured (e.g. by brazing or welding) to the base of the blade root. The plate 30 is pierced by calibration holes 32 that are placed in register with the air admission openings once the plate is in position. Depending on the sections of the holes 32 in the plate, it is thus possible to calibrate accurately the flow rates of air fed to the cavities of the internal cooling circuit(s) of the blade.
- such a calibration plate 30 is fastened at the end 26 a of the common cavity 26 as shown in FIGS. 3A and 3B .
- the advantage of mounting the calibration plate at the end of the common cavity is that it enables air flow to become uniform in the common cavity before feeding the radial cavities or the cooling circuit(s).
- the plate 30 presents a cutout 34 (e.g. formed at one of its corners, as shown in FIG. 2B ), and the common cavity 26 presents, in right section, a shape that is substantially identical to the shape of the plate (in FIG. 2B , one of the corners of the cavity has additional matter 28 of a shape that is complementary to the cutout 34 in the plate).
- a cutout 34 e.g. formed at one of its corners, as shown in FIG. 2B
- the common cavity 26 presents, in right section, a shape that is substantially identical to the shape of the plate (in FIG. 2B , one of the corners of the cavity has additional matter 28 of a shape that is complementary to the cutout 34 in the plate).
- FIGS. 3A and 3B show two other embodiments of the common cavity of the moving blade of the invention.
- the moving blade 10 ′, 10 ′′ is mounted between a downstream plate 36 and an upstream plate 38 , and the cooling circuits of the blade are fed with air via the upstream plate 38 , as represented by the arrow.
- the end wall 26 a of the common cavity 26 formed in the root 12 of the blade 10 ′′ for feeding air into the cavities of the internal cooling circuits slopes from upstream to downstream relative to the base 12 f of the blade root so as to facilitate feeding air to the cavity.
- the common cavity may be open in part level with its upstream wall and it may have an end wall that slopes from upstream to downstream relative to the base of the blade root.
- the common cavity may have a radial wall which is disposed to subdivide the common cavity into two sub-cavities.
- a radial wall makes it possible to provide a stiffener for the common cavity so as to improve its mechanical behavior.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A moving blade for a turbomachine, the blade comprising an aerodynamic surface extending radially between a blade root and a blade tip, and at least one internal cooling circuit made up of at least one radial cavity, at least one air admission opening formed in the blade root and opening out into the cavity(ies), and a plurality of outlet orifices opening out from the cavity(ies) and leading to the outside of the blade, the blade root having lower swellings and upper swellings defining bearing surfaces for fastening the blade to a rotor disk. The air admission openings of the cooling circuit(s) open out into a common cavity that is formed in the blade root and that extends radially from the base of the blade root at least as far as the upper swelling of said root.
Description
- The present invention relates to the general field of cooling moving blades in a turbomachine, and in particular the moving blades of the high-pressure turbine.
- It is known to provide the moving blades of a gas turbine in a turbomachine, such as the high-pressure or the low-pressure turbine, with internal cooling circuits enabling them to withstand without damage the very high temperatures to which they are subjected while the turbomachine is in operation. Thus, for a high-pressure turbine, the temperature of the gas coming from the combustion chamber can reach values much higher than those that the moving blades of the turbine can withstand without damage, which has the consequence of limiting the lifetime of the blades.
- By means of such cooling circuits, air that is introduced into the blade via its root travels through the blade, following a path formed by a plurality of cavities formed in the blade, prior to being ejected through outlet orifices that open out in the surface of the blade.
- Fabricating a gas turbine moving blade having a cooling circuit of that type by a casting process presents drawbacks. A blade of that type is generally obtained by casting a metal into a mold that contains a ceramic core having the function of reserving a location for each of the cavities constituting the cooling circuits of the blade. Unfortunately, the large number of cavities needed for cooling the blade makes it difficult to provide a ceramic core that is robust. There is therefore a significant risk that such a core will break.
- Furthermore, given the particular shape of a gas turbine moving blade, a given cavity in a cooling circuit does not lie in a single plane; the portion of the cavity situated at the root of the blade is offset from the remainder of the cavity. In other words, the cavities are curved. A result of this curvature of the cavities is that the flow of air in the cavities is disturbed, and that impedes cooling the blade.
- A main object of the present invention is thus to mitigate such drawbacks by providing a moving blade provided with internal cooling circuits that are simpler to fabricate by casting and in which the flow of air is facilitated.
- This object is achieved by a moving blade for a turbomachine, the blade comprising an aerodynamic surface extending radially between a blade root and a blade tip, and at least one internal cooling circuit made up of at least one radial cavity, at least one air admission opening formed in the blade root and opening out into the cavity(ies), and a plurality of outlet orifices opening out from the cavity(ies) and leading to the outside of the blade, the blade root having lower swellings and upper swellings defining bearing surfaces for fastening the blade to a rotor disk, wherein the air admission openings of the cooling circuit(s) open out into a common cavity that is formed in the blade root and that extends radially from the base of the blade root at least as far as the upper swelling of said root.
- The process of fabricating such a blade by casting is simplified. The ceramic core is consolidated by the presence of the location reserved for the common cavity for feeding air to the cavities of the cooling circuit(s). Furthermore, the presence of such a common cavity in the blade root avoids curving the cavities of the cooling circuit(s), thereby improving the flow of air therein. In addition, the presence of the common cavity makes it possible to make blades having a large cross-section—and thus an enlarged root—without thereby significantly increasing their weight (the purpose of using blades having a large cross-section is to reduce the total number of the moving blades in a given stage of a gas turbine).
- According to an advantageous characteristic of the invention, the common cavity has keying means for ensuring that a plate for calibrating the flow rates of air fed to the cavities of the cooling circuit(s) cannot be installed the wrong way round.
- The common cavity may be open in part through an upstream wall so as to facilitate feeding air to said common cavity.
- The end wall of the common cavity may be inclined from upstream to downstream relative to the base of the blade root in such a manner as to facilitate feeding air to said common cavity.
- Said common cavity may include a radial wall forming a stiffener disposed so as to subdivide the cavity into at least two sub-cavities.
- The invention also provides a turbomachine, and a high-pressure turbine for a turbomachine, each including a plurality of moving blades as defined above.
- Other characteristics and advantages of the present invention appear from the following description made with reference to the accompanying drawings which show an embodiment having no limiting character. In the figures:
-
FIG. 1 is a longitudinal section view of a moving blade of the invention; -
FIGS. 2A and 2B are fragmentary perspective views of the root of theFIG. 1 blade; and -
FIGS. 3A and 3B are fragmentary section views of moving blades constituting other embodiments of the invention. -
FIGS. 1 , 2A, and 2B show a movingblade 10 for a turbomachine, such as a moving blade of a high-pressure turbine. Naturally, the invention can also be applied to other moving blades of the turbomachine, for example to the low-pressure turbine blades thereof. - The
blade 10 has an aerodynamic surface that extends radially between theblade root 12 and ablade tip 14. This aerodynamic surface comprises a leadingedge 16 placed facing the flow of hot gas coming from the combustion chamber of the turbomachine, atrailing edge 18 opposite to the leadingedge 16, a pressure side face, and a suction side face, the side faces (not shown in the figures) interconnecting the leadingedge 16 and thetrailing edge 18. - The
blade 10 also has two lower swellings (or teeth) 12 a disposed laterally on either side of theblade root 12 and twoupper swellings 12 b also disposed laterally on either side of the root, theseswellings upper swellings lower neck 12 c, and the section defined between theupper swellings 12 b and the bottom face of theplatform 12 e of the root is referred to as anupper neck 12 d. - In known manner, the
blade 10 has at least one internal cooling circuit. This circuit comprises one or more cavities 20 extending radially over the full height of the blade, one or moreair admission openings 22 formed in theblade root 12 and leading to the cavity(ies) 20, and a plurality of outlet orifices 24 opening out from the cavity(ies) and leading to the outside of the blade. - In the embodiment of
FIG. 1 , there are four internal cooling circuits for the blade 10: one circuit situated in the vicinity of the leadingedge 16 of the blade and formed by tworadial cavities 20 a that are fed from an air admission opening 22 a; two circuits situated in the central portion of the blade, one of them being formed by threeradial cavities 20 b that are fed by an air admission opening 22 b, and the other being formed of two radial cavities 20 c that are fed by an air admission opening 22 c; and a circuit situated in the vicinity of thetrailing edge 18 of the blade and formed by aradial cavity 20 d which is fed by an air admission opening 22 d. - All of the cooling circuits are also provided with outlet orifices, respectively referenced 24 a to 24 d, that open out from the
radial cavities 20 a to 20 d and lead to the outside of the blade. Naturally, the number of cooling circuits and the quantities of radial cavities, air admission openings, and outlet orifices making up each of the circuits could be different. - The
blade 10 is typically obtained by casting a metal in a mold containing a ceramic core that has the function of occupying the positions of the radial cavities 20 or of the internal cooling circuits of the blade - According to the invention, the air admission openings 22 of the internal cooling circuit(s) of the
blade 10 all open out into acommon cavity 26 formed in theblade root 12. - The presence of such a
common cavity 26 in the blade root presents numerous advantages. Firstly, the process of fabricating the blade by casting is simplified. The dimensions of this common cavity ensure that the ceramic core needed for this type of fabrication process is consolidated in the location reserved for the common cavity. In addition, the presence of a common cavity makes it possible to improve the flow of air in the cavities of the blade cooling circuit. Finally, the presence of the common cavity makes it possible to make a blade with an enlarged root without significantly increasing its weight. - The
common cavity 26 may present a shape that is substantially in the form of a rectangular parallelepiped, as shown inFIGS. 1 , 2A, and 2B. By way of example, such a common cavity may present a section area of about 2000 square millimeters (mm2), the cavities of the cooling circuit(s) generally having sections of about 4 mm2 to 30 mm2. - As shown in
FIG. 1 , thecommon cavity 26 extends radially from thebase 12 f of theblade root 12 at least as far as theupper swellings 12 b thereof. This disposition makes it possible to obtain a cavity that is “tall”, thereby limiting head losses in feeding thecooling cavities 20 a to 20 d. In addition, the feed of cooling air to the cavities is more uniform. - According to an advantageous characteristic of the invention, the
common cavity 26 has keying means 28 to ensure that aplate 30 for calibrating the flow rates of air feeding the cavities 20 or the internal cooling circuit(s) of the blade can be fitted in a correct orientation only. - The use of a
plate 30 for calibrating the flow rates of air feeding the cavities or the internal cooling circuit(s) of a blade is well known in itself. Typically, it is constituted by ametal plate 30 that is secured (e.g. by brazing or welding) to the base of the blade root. Theplate 30 is pierced bycalibration holes 32 that are placed in register with the air admission openings once the plate is in position. Depending on the sections of theholes 32 in the plate, it is thus possible to calibrate accurately the flow rates of air fed to the cavities of the internal cooling circuit(s) of the blade. - In the context of the invention, such a
calibration plate 30 is fastened at theend 26 a of thecommon cavity 26 as shown inFIGS. 3A and 3B . The advantage of mounting the calibration plate at the end of the common cavity is that it enables air flow to become uniform in the common cavity before feeding the radial cavities or the cooling circuit(s). - In order to provide keying for said calibration plate 30 (in order to ensure that the plate is not mounted the wrong way round), the
plate 30 presents a cutout 34 (e.g. formed at one of its corners, as shown inFIG. 2B ), and thecommon cavity 26 presents, in right section, a shape that is substantially identical to the shape of the plate (inFIG. 2B , one of the corners of the cavity hasadditional matter 28 of a shape that is complementary to thecutout 34 in the plate). - It can easily be understood from
FIG. 2B that it is not possible to mount thecalibration plate 30 the wrong way round. Thus, any risk of error in calibrating the flow rates of air feeding the cavities or the internal cooling circuit(s) of the blade is avoided. -
FIGS. 3A and 3B show two other embodiments of the common cavity of the moving blade of the invention. In these figures, the movingblade 10′, 10″ is mounted between adownstream plate 36 and anupstream plate 38, and the cooling circuits of the blade are fed with air via theupstream plate 38, as represented by the arrow. - In the variant embodiment of
FIG. 3A , thecommon cavity 26 formed in theroot 12 of theblade 10′ for feeding air to the cavities of the internal cooling circuits is open in part level with theupstream wall 26 b so as to facilitate feeding air thereto. - In the variant embodiment of
FIG. 3B , theend wall 26 a of thecommon cavity 26 formed in theroot 12 of theblade 10″ for feeding air into the cavities of the internal cooling circuits slopes from upstream to downstream relative to the base 12 f of the blade root so as to facilitate feeding air to the cavity. - Naturally, these two variant embodiments for the common cavity can be combined: it may be open in part level with its upstream wall and it may have an end wall that slopes from upstream to downstream relative to the base of the blade root.
- In yet another variant embodiment of the common cavity (not shown in the figures), the common cavity may have a radial wall which is disposed to subdivide the common cavity into two sub-cavities. Such a radial wall makes it possible to provide a stiffener for the common cavity so as to improve its mechanical behavior.
Claims (7)
1. A moving blade for a turbomachine, the blade comprising an aerodynamic surface extending radially between a blade root and a blade tip, and at least one internal cooling circuit made up of at least one radial cavity, at least one air admission opening formed in the blade root and opening out into the cavity(ies), and a plurality of outlet orifices opening out from the cavity(ies) and leading to the outside of the blade, the blade root having lower swellings and upper swellings defining bearing surfaces for fastening the blade to a rotor disk, wherein the air admission openings of the cooling circuit(s) open out into a common cavity that is formed in the blade root and that extends radially from the base of the blade root at least as far as the upper swelling of said root.
2. A blade according to claim 1 , wherein the common cavity has keying means for ensuring that a plate for calibrating the flow rates of air fed to the cavities of the cooling circuit(s) cannot be installed the wrong way round.
3. A blade according to claim 1 , wherein the common cavity is open in part through an upstream wall so as to facilitate feeding air to said common cavity.
4. A blade according to claim 1 , wherein the end wall of the common cavity is inclined from upstream to downstream relative to the base of the blade root in such a manner as to facilitate feeding air to said common cavity.
5. A blade according to claim 1 , wherein said common cavity includes a radial wall forming a stiffener disposed so as to subdivide the cavity into at least two sub-cavities.
6. A turbomachine high-pressure turbine, including a plurality of moving blades according to claim 1 .
7. A turbomachine, including a plurality of moving blades according to claim 1 .
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0650800 | 2006-03-08 | ||
FR0650800A FR2898384B1 (en) | 2006-03-08 | 2006-03-08 | MOBILE TURBINE DRAWER WITH COMMON CAVITY COOLING AIR SUPPLY |
Publications (1)
Publication Number | Publication Date |
---|---|
US20070212228A1 true US20070212228A1 (en) | 2007-09-13 |
Family
ID=36463518
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/682,517 Abandoned US20070212228A1 (en) | 2006-03-08 | 2007-03-06 | Moving blade for a turbomachine, the blade having a common cooling air feed cavity |
Country Status (4)
Country | Link |
---|---|
US (1) | US20070212228A1 (en) |
EP (1) | EP1832712A1 (en) |
CA (1) | CA2581007A1 (en) |
FR (1) | FR2898384B1 (en) |
Cited By (13)
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US20110194944A1 (en) * | 2008-10-22 | 2011-08-11 | Snecma | Turbine blade equipped with means of adjusting its cooling fluid flow rate |
US20120163995A1 (en) * | 2010-12-27 | 2012-06-28 | Wardle Brian Kenneth | Turbine blade |
EP2535515A1 (en) * | 2011-06-16 | 2012-12-19 | Siemens Aktiengesellschaft | Rotor blade root section with cooling passage and method for supplying cooling fluid to a rotor blade |
US20120321461A1 (en) * | 2010-12-21 | 2012-12-20 | Avio S.P.A. | Gas Turbine Bladed Rotor For Aeronautic Engines And Method For Cooling Said Bladed Rotor |
US8622702B1 (en) * | 2010-04-21 | 2014-01-07 | Florida Turbine Technologies, Inc. | Turbine blade with cooling air inlet holes |
AU2011250788B2 (en) * | 2010-11-29 | 2015-02-05 | General Electric Technology Gmbh | Blade for a gas turbine, method for manufacturing said blade and gas turbine with such a blade |
US20170009590A1 (en) * | 2015-07-06 | 2017-01-12 | Siemens Aktiengesellschaft | Orifice element for turbine stator and/or rotor vanes |
WO2019102556A1 (en) * | 2017-11-22 | 2019-05-31 | 東芝エネルギーシステムズ株式会社 | Turbine blade and turbine |
US20190292918A1 (en) * | 2016-06-02 | 2019-09-26 | Safran Aircraft Engines | Turbine vane including a cooling-air intake portion including a helical element for swirling the cooling air |
CN111058901A (en) * | 2018-10-16 | 2020-04-24 | 斗山重工业建设有限公司 | Turbine stator blade, turbine rotor blade and gas turbine comprising same |
US11499440B2 (en) | 2020-08-21 | 2022-11-15 | Doosan Enerbility Co., Ltd | Turbine vane and gas turbine including the same |
WO2023140268A1 (en) * | 2022-01-19 | 2023-07-27 | 三菱重工業株式会社 | Turbine rotor blade |
US11933193B2 (en) | 2021-01-08 | 2024-03-19 | Ge Avio S.R.L. | Turbine engine with an airfoil having a set of dimples |
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US8172533B2 (en) * | 2008-05-14 | 2012-05-08 | United Technologies Corporation | Turbine blade internal cooling configuration |
FR2995342B1 (en) * | 2012-09-13 | 2018-03-16 | Safran Aircraft Engines | AUBE COOLED HIGH PRESSURE TURBINE |
FR3106624B1 (en) * | 2020-01-24 | 2022-02-18 | Safran Aircraft Engines | improved cooling anomaly detection device for an aircraft turbomachine |
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US2641440A (en) * | 1947-11-18 | 1953-06-09 | Chrysler Corp | Turbine blade with cooling means and carrier therefor |
DE68906594T2 (en) * | 1988-04-25 | 1993-08-26 | United Technologies Corp | DUST SEPARATOR FOR AN AIR COOLED SHOVEL. |
JPH10280904A (en) * | 1997-04-01 | 1998-10-20 | Mitsubishi Heavy Ind Ltd | Cooled rotor blade for gas turbine |
US6561758B2 (en) * | 2001-04-27 | 2003-05-13 | General Electric Company | Methods and systems for cooling gas turbine engine airfoils |
DE10217389A1 (en) * | 2002-04-18 | 2003-10-30 | Siemens Ag | turbine blade |
US6932570B2 (en) * | 2002-05-23 | 2005-08-23 | General Electric Company | Methods and apparatus for extending gas turbine engine airfoils useful life |
DE102004002327A1 (en) * | 2004-01-16 | 2005-08-04 | Alstom Technology Ltd | Cooled shovel for a gas turbine |
MY140195A (en) * | 2004-03-30 | 2009-11-30 | Alstom Technology Ltd | Arrangement for the admission of cooling air to a rotating component, in particular for a moving blade in a rotary machine |
-
2006
- 2006-03-08 FR FR0650800A patent/FR2898384B1/en active Active
-
2007
- 2007-03-02 EP EP07103424A patent/EP1832712A1/en not_active Withdrawn
- 2007-03-06 US US11/682,517 patent/US20070212228A1/en not_active Abandoned
- 2007-03-07 CA CA002581007A patent/CA2581007A1/en not_active Abandoned
Cited By (26)
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US20190292918A1 (en) * | 2016-06-02 | 2019-09-26 | Safran Aircraft Engines | Turbine vane including a cooling-air intake portion including a helical element for swirling the cooling air |
US11988108B2 (en) * | 2016-06-02 | 2024-05-21 | Safran Aircraft Engines | Turbine vane including a cooling-air intake portion including a helical element for swirling the cooling air |
WO2019102556A1 (en) * | 2017-11-22 | 2019-05-31 | 東芝エネルギーシステムズ株式会社 | Turbine blade and turbine |
US11162371B2 (en) | 2018-10-16 | 2021-11-02 | Doosan Heavy Industries & Construction Co., Ltd. | Turbine vane, turbine blade, and gas turbine including the same |
KR102152415B1 (en) * | 2018-10-16 | 2020-09-04 | 두산중공업 주식회사 | Turbine vane and turbine blade and gas turbine comprising the same |
KR20200042622A (en) * | 2018-10-16 | 2020-04-24 | 두산중공업 주식회사 | Turbine vane and turbine blade and gas turbine comprising the same |
CN111058901B (en) * | 2018-10-16 | 2022-06-17 | 斗山重工业建设有限公司 | Turbine stator blade, turbine rotor blade and gas turbine comprising same |
US11525362B2 (en) | 2018-10-16 | 2022-12-13 | Doosan Enerbility Co., Ltd. | Turbine vane, turbine blade, and gas turbine including the same |
CN111058901A (en) * | 2018-10-16 | 2020-04-24 | 斗山重工业建设有限公司 | Turbine stator blade, turbine rotor blade and gas turbine comprising same |
US11499440B2 (en) | 2020-08-21 | 2022-11-15 | Doosan Enerbility Co., Ltd | Turbine vane and gas turbine including the same |
US11933193B2 (en) | 2021-01-08 | 2024-03-19 | Ge Avio S.R.L. | Turbine engine with an airfoil having a set of dimples |
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Also Published As
Publication number | Publication date |
---|---|
FR2898384B1 (en) | 2011-09-16 |
EP1832712A1 (en) | 2007-09-12 |
CA2581007A1 (en) | 2007-09-08 |
FR2898384A1 (en) | 2007-09-14 |
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