US20150078900A1 - Turbine blade with airfoil tip having cutting tips - Google Patents
Turbine blade with airfoil tip having cutting tips Download PDFInfo
- Publication number
- US20150078900A1 US20150078900A1 US14/031,457 US201314031457A US2015078900A1 US 20150078900 A1 US20150078900 A1 US 20150078900A1 US 201314031457 A US201314031457 A US 201314031457A US 2015078900 A1 US2015078900 A1 US 2015078900A1
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- United States
- Prior art keywords
- abradable coating
- cutting tips
- coating cutting
- tip
- turbine blade
- 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.)
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Images
Classifications
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- 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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/21—Three-dimensional pyramidal
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/22—Three-dimensional parallelepipedal
- F05D2250/221—Three-dimensional parallelepipedal cubic
Definitions
- This invention is directed generally to turbine blades, and more particularly to tip configurations of turbine blades in gas turbine engines.
- gas turbine engines typically include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power.
- Combustors often operate at high temperatures that may exceed 2,500 degrees Fahrenheit.
- Typical turbine combustor configurations expose turbine blade assemblies to these high temperatures.
- turbine blades must be made of materials capable of withstanding such high temperatures.
- turbine blades often contain cooling systems for prolonging the life of the blades and reducing the likelihood of failure as a result of excessive temperatures.
- turbine blades are formed from a root portion at one end and an elongated portion forming a blade that extends outwardly from a platform coupled to the root portion at an opposite end of the turbine blade.
- the blade is ordinarily composed of a tip opposite the root section, a leading edge, and a trailing edge.
- the tip of a turbine blade often has a tip seals to reduce the gap between ring segments and blades in the gas path of the turbine.
- the tip seals are often referred to as squealer tips and are frequently incorporated onto the tips of blades to help reduce pressure losses between turbine stages. These features are designed to minimize the gap between the blade tip and the ring segment. Nonetheless, during startup, the blade tip often contacts the ring segments and causes wear on the blade tip, which damages the blade. Thus, a need exists for accommodating startup conditions without damaging the turbine blades.
- a turbine blade having a squealer tip at a radially outer end of the turbine blade with a plurality of abradable coating cutting tips extending radially therefrom toward a ring segment is disclosed.
- the abradable coating cutting tips may cut into an abradable coating on the ring segments of the turbine engine that are positioned radially outward from the turbine blade.
- the plurality of abradable coating cutting tips may include one or more cutting arrises extending from the squealer tip to an outermost tip of the abradable coating cutting tips.
- the turbine blade may be formed from a generally elongated blade having a leading edge, a trailing edge, a tip at a first end, a root coupled to the blade at a second end generally opposite the first end for supporting the blade and for coupling the blade to a disc.
- the blade may also include a squealer tip coupled to the tip at the first end.
- the squealer tip may include a plurality of abradable coating cutting tips that extend radially from the squealer tip toward a ring segment positioned radially outward from the generally elongated blade.
- the plurality of abradable coating cutting tips may be formed into at least two rows of abradable coating cutting tips extending generally orthogonal to a flow of combustion exhaust gases between the squealer tip and the ring segment.
- a second row of abradable coating cutting tips may be positioned downstream from a first row of abradable coating cutting tips and may be offset orthogally to the flow of combustion exhaust gases relative to the first row of abradable coating cutting tips.
- one or more of the abradable coating cutting tips may have at least one cutting arrises extending from the squealer tip to an outermost tip of the abradable coating cutting tip. In another embodiment, one or more of the abradable coating cutting tips have at least three cutting arrises extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips.
- a first cutting arris may be positioned on an upstream side of the abradable coating cutting tip.
- a second cutting arris may extend from the squealer tip to the outermost tip of the abradable coating cutting tip at a first intersection between the upstream side and a downstream side of the abradable coating cutting tip.
- a third cutting arris may extend from the squealer tip to the outermost tip of the abradable coating cutting tip at a second intersection between the upstream side and the downstream side of the abradable coating cutting tip.
- the second intersection may be on an opposite side of the tip from the first side.
- one or more of the plurality of abradable coating cutting tips may have a pyramid shape. In another embodiment, each of the plurality of abradable coating cutting tips may have a pyramid shape. At least one of the plurality of abradable coating cutting tips may extend from the squealer tip a distance of at least 125 microns. In another embodiment, at least one of the plurality of abradable coating cutting tips may extend from the squealer tip a distance of at least 250 microns. In a further embodiment, at least one of the plurality of abradable coating cutting tips may extend from the squealer tip a distance of 1000 microns, which is 1 millimeter.
- the plurality of abradable coating cutting tips may extend from the squealer tip a distance of at least 125 microns and less than 1,025 microns.
- the plurality of abradable coating cutting tips may be formed from a knurled surface on the radially outer end of the squealer tip.
- At least one of the plurality of abradable coating cutting tips is formed from a plurality of planar surfaces, wherein adjacent planar surfaces intersect to form a cutting arris. At least one of the plurality of abradable coating cutting tips may be formed from at least four planar surfaces. Adjacent abradable coating cutting tips may be separated at an outer surface of the squealer tip by a linear line. The plurality of abradable coating cutting tips may be separated at an outer surface of the squealer tip into rows by a plurality of linear lines positioned in a first orientation and a plurality of linear lines positioned in a second orientation. The second orientation may be orthogonal to the first orientation. The first orientation and the second orientation may also be nonparallel and nonorthogonal relative to a direction of flow of combustion exhaust gases.
- An advantage of this invention is that the improved clearance control increases engine efficiency and power by improving the ability of the blade tips to engrave or cut the abradable material on the stationary component.
- Another advantage of this invention is that the abradable coating cutting tips cut into the abradable coating on the radially inner surface of the ring segments producing a profile that corresponds with the abradable coating cutting tips extending from the turbine blade.
- Yet another advantage of this invention is that the profile of the turbine blade corresponds exactly to the swept profile in the ring segments, thereby improving clearance control.
- FIG. 1 is a perspective view of a turbine blade having features according to the instant invention.
- FIG. 2 is a detailed cross-sectional view of a tubine blade tip adjacent to a radialy outward positioned ring segment, whereby the scale of the abradable coating cutting tips are enlarged so that they can been seen.
- FIG. 3 is detailed top view of a portion of the tip of the turbine blade with abradable coating cutting tips.
- FIG. 4 is a detailed side view of the portion of the tip of the turbine blade with abradable coating cutting tips shown in FIG. 3 .
- FIG. 5 is detailed top view of a portion of another embodiment of the tip of the turbine blade with abradable coating cutting tips.
- FIG. 6 is a detailed side view of the portion of the tip of the turbine blade with abradable coating cutting tips shown in FIG. 5 .
- FIG. 7 is photograph of the results of test of a turbine blade contacting a strip of material, whereby the top strip of material was struck by a flat metal turbine blade tip, the middle strip of material was struck by a turbine blade tip having abradable coating cutting tips with a height of about 125 microns, and the bottom strip of material was struck by a turbine blade tip having abradable coating cutting tips with a height of about 250 microns.
- FIG. 8 is a perspective view of a portion of the tip of the turbine blade with abradable coating cutting tips.
- a turbine blade 10 having a squealer tip 12 at a radially outer end 14 of the turbine blade 16 with a plurality of abradable coating cutting tips 18 extending radially therefrom toward a ring segment 20 is disclosed.
- the abradable coating cutting tips 18 may cut into an abradable coating 22 on the ring segments 20 of the turbine engine that are positioned radially outward from the turbine blade 10 , as shown in FIG. 2 .
- the plurality of abradable coating cutting tips 18 may include one or more cutting arrises 28 extending from the squealer tip 12 to an outermost tip 30 of the abradable coating cutting tips 18 .
- the turbine blade 10 may be formed from any appropriate configuration.
- the turbine blade 10 may be formed from a generally elongated blade 32 having a leading edge 34 , a trailing edge 36 , a tip 38 at a first end 14 , a root 42 coupled to the blade 32 at a second end 44 generally opposite the first end 14 for supporting the blade 32 and for coupling the blade 32 to a disc.
- the turbine blade 10 may include a squealer tip 12 coupled to the tip 38 at the first end 40 .
- the squealer tip 12 may include a plurality of abradable coating cutting tips 18 that extend radially from the squealer tip 12 toward one or more ring segments 20 positioned radially outward from the generally elongated blade 32 .
- the abradable coating cutting tips 18 may be formed into at least two rows 46 , 48 of abradable coating cutting tips 18 extending generally orthogonal to a flow of combustion exhaust gases 50 between the squealer tip 12 and the ring segment 20 .
- a second row 48 of abradable coating cutting tips 18 may be positioned downstream from a first row 46 of abradable coating cutting tips 18 and may be offset orthogally to the flow of combustion exhaust gases 50 relative to the first row of abradable coating cutting tips 46 .
- One or more of the abradable coating cutting tips 18 may have one or more cutting arrises 28 extending from the squealer tip 12 to an outermost tip 30 of the abradable coating cutting tips 18 , as shown in FIGS. 1-6 and 8 .
- one or more of the abradable coating cutting tips 18 may have at least three cutting arrises 28 extending from the squealer tip 12 to the outermost tip 30 of the abradable coating cutting tip 18 .
- a first cutting arris 54 may be positioned on an upstream side 56 of the abradable coating cutting tip 18 .
- a second cutting arris 58 may extend from the squealer tip 12 to the outermost tip 30 of the abradable coating cutting tip 18 at a first intersection 60 between the upstream side 56 and a downstream side 62 of the abradable coating cutting tip 18 .
- a third cutting arris 64 may extend from the squealer tip 12 to the outermost tip 30 of the abradable coating cutting tip 18 at a second intersection 66 between the upstream side 56 and the downstream side 62 of the abradable coating cutting tip 18 .
- the second intersection 66 may be on an opposite side of the abradable coating cutting tip 18 from a first side 68 with the first intersection 60 .
- one or more of the abradable coating cutting tips 18 may have a pyramid shape with a wide base 70 coupled to the squealer tip 12 and tip 30 at an opposite radially outermost end.
- each of the plurality of abradable coating cutting tips 18 may have a pyramid shape.
- One or more of the abradable coating cutting tips 18 may be formed from a plurality of planar surfaces 72 wherein adjacent planar surfaces 72 intersect to form a cutting arris 28 .
- one or more of the abradable coating cutting tips 18 may be formed from at least four planar surfaces 72 .
- the four planar surfaces 72 may each be separated by a cutting arris 28 for a total of four cutting arrises 28 .
- an abradable coating cutting tip 18 may include more than four planar sides or less than four planar sides and similarly, more or less than four cutting arrises 28 .
- Adjacent abradable coating cutting tips 18 may be separated at an outer surface 74 of the squealer tip 12 by a linear line 76 .
- the abradable coating cutting tips 18 may be separated at the outer surface 74 of the squealer tip 12 into rows by a plurality of linear lines 76 positioned in a first orientation 78 and a plurality of linear lines 76 positioned in a second orientation 80 , wherein the second orientation 80 is orthogonal to the first orientation 78 .
- the first orientation 78 and the second orientation 80 may be nonparallel and nonorthogonal relative to a direction of flow 50 of combustion exhaust gases.
- the abradable coating cutting tips 18 extend from the squealer tip 12 a distance of about 5 mils, which is about 125 microns. In another embodiment, the abradable coating cutting tips 18 may extend from the squealer tip 12 a distance of about 10 mils, which is about 250 microns. In a further embodiment, at least one of the plurality of abradable coating cutting tips may extend from the squealer tip a distance of 1000 microns, which is 1 millimeter. In another embodiment, the abradable coating cutting tips 18 may extend from the squealer tip 12 a distance of at least 125 microns and less than 1,025 microns. In at least one embodiment, the abradable coating cutting tips 18 form a knurled surface on the radially outer end of the squealer tip 12 .
- the abradable coating cutting tips 18 may be formed by machining the abradable coating cutting tips 18 in the tip 38 of the generally elongated blade 32 .
- the machining the abradable coating cutting tips 18 may be formed by a grinding or milling operation. The grinding or milling operation may produce a pattern of pyramidal abradable coating cutting tips 18 ,
- the turbine blades 10 are coupled to a rotor assembly that rotates, while ring segments 20 form a boundary radially outward from the turbine blades 10 .
- the turbine blade and ring segments are heated and thermally expand.
- the turbine blade 10 may contact the ring segments 20 as the turbine blade 10 is rotated.
- the abradable coating cutting tips 18 cut into the abradable coating on the radially inner surface of the ring segments 20 producing a profile that corresponds with the abradable coating cutting tips 18 extending from the turbine blade 10 .
- the profile of the turbine blade 10 corresponds exactly to the swept profile in the ring segments 20 , thereby improving clearance control.
- the improved clearance control increases engine efficiency and power by improving the ability of the blade tips to engrave or cut the abradable material on the stationary component.
Abstract
A turbine blade having a squealer tip at a radially outer end of the turbine blade with a plurality of abradable coating cutting tips extending radially therefrom toward a ring segment is disclosed. During operation, the abradable coating cutting tips may cut into an abradable coating on the ring segments of the turbine engine that are positioned radially outward from the turbine blade. The plurality of abradable coating cutting tips may include one or more cutting arrises extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips.
Description
- Development of this invention was supported in part by the United States Department of Energy, Advanced Hydrogen Turbine Development Program, Contract No. DE-FC26-05NT42644. Accordingly, the United States Government may have certain rights in this invention.
- This invention is directed generally to turbine blades, and more particularly to tip configurations of turbine blades in gas turbine engines.
- Typically, gas turbine engines include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power. Combustors often operate at high temperatures that may exceed 2,500 degrees Fahrenheit. Typical turbine combustor configurations expose turbine blade assemblies to these high temperatures. As a result, turbine blades must be made of materials capable of withstanding such high temperatures. In addition, turbine blades often contain cooling systems for prolonging the life of the blades and reducing the likelihood of failure as a result of excessive temperatures.
- Typically, turbine blades are formed from a root portion at one end and an elongated portion forming a blade that extends outwardly from a platform coupled to the root portion at an opposite end of the turbine blade. The blade is ordinarily composed of a tip opposite the root section, a leading edge, and a trailing edge. The tip of a turbine blade often has a tip seals to reduce the gap between ring segments and blades in the gas path of the turbine. The tip seals are often referred to as squealer tips and are frequently incorporated onto the tips of blades to help reduce pressure losses between turbine stages. These features are designed to minimize the gap between the blade tip and the ring segment. Nonetheless, during startup, the blade tip often contacts the ring segments and causes wear on the blade tip, which damages the blade. Thus, a need exists for accommodating startup conditions without damaging the turbine blades.
- A turbine blade having a squealer tip at a radially outer end of the turbine blade with a plurality of abradable coating cutting tips extending radially therefrom toward a ring segment is disclosed. During operation, the abradable coating cutting tips may cut into an abradable coating on the ring segments of the turbine engine that are positioned radially outward from the turbine blade. The plurality of abradable coating cutting tips may include one or more cutting arrises extending from the squealer tip to an outermost tip of the abradable coating cutting tips. By cutting into the adjacent abradable coating, the abradable coating cutting tips enable the turbine engine to continue operating without losing efficiency.
- The turbine blade may be formed from a generally elongated blade having a leading edge, a trailing edge, a tip at a first end, a root coupled to the blade at a second end generally opposite the first end for supporting the blade and for coupling the blade to a disc. The blade may also include a squealer tip coupled to the tip at the first end. The squealer tip may include a plurality of abradable coating cutting tips that extend radially from the squealer tip toward a ring segment positioned radially outward from the generally elongated blade. The plurality of abradable coating cutting tips may be formed into at least two rows of abradable coating cutting tips extending generally orthogonal to a flow of combustion exhaust gases between the squealer tip and the ring segment. A second row of abradable coating cutting tips may be positioned downstream from a first row of abradable coating cutting tips and may be offset orthogally to the flow of combustion exhaust gases relative to the first row of abradable coating cutting tips.
- In at least one embodiment, one or more of the abradable coating cutting tips may have at least one cutting arrises extending from the squealer tip to an outermost tip of the abradable coating cutting tip. In another embodiment, one or more of the abradable coating cutting tips have at least three cutting arrises extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips. A first cutting arris may be positioned on an upstream side of the abradable coating cutting tip. A second cutting arris may extend from the squealer tip to the outermost tip of the abradable coating cutting tip at a first intersection between the upstream side and a downstream side of the abradable coating cutting tip. A third cutting arris may extend from the squealer tip to the outermost tip of the abradable coating cutting tip at a second intersection between the upstream side and the downstream side of the abradable coating cutting tip. The second intersection may be on an opposite side of the tip from the first side.
- In at least one embodiment, one or more of the plurality of abradable coating cutting tips may have a pyramid shape. In another embodiment, each of the plurality of abradable coating cutting tips may have a pyramid shape. At least one of the plurality of abradable coating cutting tips may extend from the squealer tip a distance of at least 125 microns. In another embodiment, at least one of the plurality of abradable coating cutting tips may extend from the squealer tip a distance of at least 250 microns. In a further embodiment, at least one of the plurality of abradable coating cutting tips may extend from the squealer tip a distance of 1000 microns, which is 1 millimeter. In yet another embodiment, the plurality of abradable coating cutting tips may extend from the squealer tip a distance of at least 125 microns and less than 1,025 microns. The plurality of abradable coating cutting tips may be formed from a knurled surface on the radially outer end of the squealer tip.
- In another embodiment, at least one of the plurality of abradable coating cutting tips is formed from a plurality of planar surfaces, wherein adjacent planar surfaces intersect to form a cutting arris. At least one of the plurality of abradable coating cutting tips may be formed from at least four planar surfaces. Adjacent abradable coating cutting tips may be separated at an outer surface of the squealer tip by a linear line. The plurality of abradable coating cutting tips may be separated at an outer surface of the squealer tip into rows by a plurality of linear lines positioned in a first orientation and a plurality of linear lines positioned in a second orientation. The second orientation may be orthogonal to the first orientation. The first orientation and the second orientation may also be nonparallel and nonorthogonal relative to a direction of flow of combustion exhaust gases.
- An advantage of this invention is that the improved clearance control increases engine efficiency and power by improving the ability of the blade tips to engrave or cut the abradable material on the stationary component.
- Another advantage of this invention is that the abradable coating cutting tips cut into the abradable coating on the radially inner surface of the ring segments producing a profile that corresponds with the abradable coating cutting tips extending from the turbine blade.
- Yet another advantage of this invention is that the profile of the turbine blade corresponds exactly to the swept profile in the ring segments, thereby improving clearance control.
- These and other embodiments are described in more detail below.
- The accompanying drawings, which are incorporated in and form a part of the specification, illustrate embodiments of the presently disclosed invention and, together with the description, disclose the principles of the invention.
-
FIG. 1 is a perspective view of a turbine blade having features according to the instant invention. -
FIG. 2 is a detailed cross-sectional view of a tubine blade tip adjacent to a radialy outward positioned ring segment, whereby the scale of the abradable coating cutting tips are enlarged so that they can been seen. -
FIG. 3 is detailed top view of a portion of the tip of the turbine blade with abradable coating cutting tips. -
FIG. 4 is a detailed side view of the portion of the tip of the turbine blade with abradable coating cutting tips shown inFIG. 3 . -
FIG. 5 is detailed top view of a portion of another embodiment of the tip of the turbine blade with abradable coating cutting tips. -
FIG. 6 is a detailed side view of the portion of the tip of the turbine blade with abradable coating cutting tips shown inFIG. 5 . -
FIG. 7 is photograph of the results of test of a turbine blade contacting a strip of material, whereby the top strip of material was struck by a flat metal turbine blade tip, the middle strip of material was struck by a turbine blade tip having abradable coating cutting tips with a height of about 125 microns, and the bottom strip of material was struck by a turbine blade tip having abradable coating cutting tips with a height of about 250 microns. -
FIG. 8 is a perspective view of a portion of the tip of the turbine blade with abradable coating cutting tips. - As shown in
FIGS. 1-8 , aturbine blade 10 having asquealer tip 12 at a radiallyouter end 14 of the turbine blade 16 with a plurality of abradablecoating cutting tips 18 extending radially therefrom toward a ring segment 20 is disclosed. During operation, the abradablecoating cutting tips 18 may cut into an abradable coating 22 on the ring segments 20 of the turbine engine that are positioned radially outward from theturbine blade 10, as shown inFIG. 2 . The plurality of abradablecoating cutting tips 18 may include one ormore cutting arrises 28 extending from thesquealer tip 12 to anoutermost tip 30 of the abradablecoating cutting tips 18. By cutting into the adjacent abradable coating 22, the abradablecoating cutting tips 18 enable the turbine engine to continue operating with losing efficiency. - The
turbine blade 10 may be formed from any appropriate configuration. For instance, in at least one embodiment, theturbine blade 10 may be formed from a generally elongatedblade 32 having a leadingedge 34, a trailingedge 36, atip 38 at afirst end 14, aroot 42 coupled to theblade 32 at asecond end 44 generally opposite thefirst end 14 for supporting theblade 32 and for coupling theblade 32 to a disc. Theturbine blade 10 may include asquealer tip 12 coupled to thetip 38 at the first end 40. Thesquealer tip 12 may include a plurality of abradablecoating cutting tips 18 that extend radially from thesquealer tip 12 toward one or more ring segments 20 positioned radially outward from the generally elongatedblade 32. - In at least one embodiment, the abradable
coating cutting tips 18 may be formed into at least tworows coating cutting tips 18 extending generally orthogonal to a flow ofcombustion exhaust gases 50 between thesquealer tip 12 and the ring segment 20. Asecond row 48 of abradablecoating cutting tips 18 may be positioned downstream from afirst row 46 of abradablecoating cutting tips 18 and may be offset orthogally to the flow ofcombustion exhaust gases 50 relative to the first row of abradablecoating cutting tips 46. - One or more of the abradable
coating cutting tips 18 may have one ormore cutting arrises 28 extending from thesquealer tip 12 to anoutermost tip 30 of the abradablecoating cutting tips 18, as shown inFIGS. 1-6 and 8. In at least one embodiment, as shown inFIGS. 5 and 8 , one or more of the abradablecoating cutting tips 18 may have at least three cuttingarrises 28 extending from thesquealer tip 12 to theoutermost tip 30 of the abradablecoating cutting tip 18. A first cuttingarris 54 may be positioned on anupstream side 56 of the abradablecoating cutting tip 18. A second cuttingarris 58 may extend from thesquealer tip 12 to theoutermost tip 30 of the abradablecoating cutting tip 18 at afirst intersection 60 between theupstream side 56 and adownstream side 62 of the abradablecoating cutting tip 18. A third cuttingarris 64 may extend from thesquealer tip 12 to theoutermost tip 30 of the abradablecoating cutting tip 18 at asecond intersection 66 between theupstream side 56 and thedownstream side 62 of the abradablecoating cutting tip 18. Thesecond intersection 66 may be on an opposite side of the abradablecoating cutting tip 18 from afirst side 68 with thefirst intersection 60. - In at least one embodiment, as shown in
FIGS. 3 , 5 and 8, one or more of the abradablecoating cutting tips 18 may have a pyramid shape with awide base 70 coupled to thesquealer tip 12 andtip 30 at an opposite radially outermost end. In another embodiment, each of the plurality of abradablecoating cutting tips 18 may have a pyramid shape. One or more of the abradablecoating cutting tips 18 may be formed from a plurality ofplanar surfaces 72 wherein adjacentplanar surfaces 72 intersect to form a cuttingarris 28. In an embodiment, where the abradablecoating cutting tips 18 are formed of a pyramid shape, one or more of the abradablecoating cutting tips 18 may be formed from at least fourplanar surfaces 72. In such an embodiment, the fourplanar surfaces 72 may each be separated by a cuttingarris 28 for a total of four cuttingarrises 28. In other embodiments, an abradablecoating cutting tip 18 may include more than four planar sides or less than four planar sides and similarly, more or less than four cuttingarrises 28. - Adjacent abradable
coating cutting tips 18 may be separated at anouter surface 74 of thesquealer tip 12 by alinear line 76. In at least one embodiment, the abradablecoating cutting tips 18 may be separated at theouter surface 74 of thesquealer tip 12 into rows by a plurality oflinear lines 76 positioned in afirst orientation 78 and a plurality oflinear lines 76 positioned in asecond orientation 80, wherein thesecond orientation 80 is orthogonal to thefirst orientation 78. Thefirst orientation 78 and thesecond orientation 80 may be nonparallel and nonorthogonal relative to a direction offlow 50 of combustion exhaust gases. - In at least one embodiment, the abradable
coating cutting tips 18 extend from the squealer tip 12 a distance of about 5 mils, which is about 125 microns. In another embodiment, the abradablecoating cutting tips 18 may extend from the squealer tip 12 a distance of about 10 mils, which is about 250 microns. In a further embodiment, at least one of the plurality of abradable coating cutting tips may extend from the squealer tip a distance of 1000 microns, which is 1 millimeter. In another embodiment, the abradablecoating cutting tips 18 may extend from the squealer tip 12 a distance of at least 125 microns and less than 1,025 microns. In at least one embodiment, the abradablecoating cutting tips 18 form a knurled surface on the radially outer end of thesquealer tip 12. - The abradable
coating cutting tips 18 may be formed by machining the abradablecoating cutting tips 18 in thetip 38 of the generally elongatedblade 32. In particular, the machining the abradablecoating cutting tips 18 may be formed by a grinding or milling operation. The grinding or milling operation may produce a pattern of pyramidal abradablecoating cutting tips 18, - During use, the
turbine blades 10 are coupled to a rotor assembly that rotates, while ring segments 20 form a boundary radially outward from theturbine blades 10. As the combustion exhaust gases flow past theturbine blades 10, the turbine blade and ring segments are heated and thermally expand. During the startup process before reaching a steady state operating condition, theturbine blade 10 may contact the ring segments 20 as theturbine blade 10 is rotated. The abradablecoating cutting tips 18 cut into the abradable coating on the radially inner surface of the ring segments 20 producing a profile that corresponds with the abradablecoating cutting tips 18 extending from theturbine blade 10. As such, the profile of theturbine blade 10 corresponds exactly to the swept profile in the ring segments 20, thereby improving clearance control. The improved clearance control increases engine efficiency and power by improving the ability of the blade tips to engrave or cut the abradable material on the stationary component. - The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention.
Claims (20)
1. A turbine blade, comprising:
a generally elongated blade having a leading edge, a trailing edge, a tip at a first end, a root coupled to the blade at a second end generally opposite the first end for supporting the blade and for coupling the blade to a disc; and
a squealer tip coupled to the tip at the first end, wherein the squealer tip includes a plurality of abradable coating cutting tips that extend radially from the squealer tip toward a ring segment positioned radially outward from the generally elongated blade.
2. The turbine blade of claim 1 , wherein the plurality of abradable coating cutting tips is formed into at least two rows of abradable coating cutting tips extending generally orthogonal to a flow of combustion exhaust gases between the squealer tip and the ring segment, and wherein a second row of abradable coating cutting tips is positioned downstream from a first row of abradable coating cutting tips and is offset orthogally to the flow of combustion exhaust gases relative to the first row of abradable coating cutting tips.
3. The turbine blade of claim 1 , wherein at least one of the abradable coating cutting tips has at least one cutting arris extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips.
4. The turbine blade of claim 3 , wherein at least one of the abradable coating cutting tips has at least three cutting arrises extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips, wherein a first cutting arris is positioned on an upstream side of the at least one of the abradable coating cutting tips, a second cutting arris extending from the squealer tip to the outermost tip of the at least one of the abradable coating cutting tips at a first intersection between the upstream side and a downstream side of the at least one of the abradable coating cutting tips, and a third cutting arris extending from the squealer tip to the outermost tip of the at least one of the abradable coating cutting tips at a second intersection between the upstream side and the downstream side of the at least one of the abradable coating cutting tips, wherein the second intersection is on an opposite side of the tip from a first side.
5. The turbine blade of claim 1 , wherein at least one of the plurality of abradable coating cutting tips has a pyramid shape.
6. The turbine blade of claim 1 , wherein at least one of the plurality of abradable coating cutting tips extends from the squealer tip a distance of at least 125 microns.
7. The turbine blade of claim 1 , wherein at least one of the plurality of abradable coating cutting tips extends from the squealer tip a distance of at least 250 microns.
8. The turbine blade of claim 1 , wherein at least one of the plurality of abradable coating cutting tips extends from the squealer tip a distance of up to 1000 microns.
9. The turbine blade of claim 1 , wherein of the plurality of abradable coating cutting tips forms a knurled surface on the radially outer end of the squealer tip.
10. The turbine blade of claim 1 , wherein at least one of the plurality of abradable coating cutting tips is formed from a plurality of planar surfaces, wherein adjacent planar surfaces intersect to form a cutting arris.
11. The turbine blade of claim 10 , wherein the at least one of the plurality of abradable coating cutting tips is formed from at least four planar surfaces.
12. The turbine blade of claim 10 , wherein adjacent abradable coating cutting tips are separated at an outer surface of the squealer tip by a linear line.
13. The turbine blade of claim 10 , wherein the plurality of abradable coating cutting tips are separated at an outer surface of the squealer tip into rows by a plurality of linear lines positioned in a first orientation and a plurality of linear lines positioned in a second orientation, wherein the second orientation is orthogonal to the first orientation.
14. The turbine blade of claim 13 , wherein the first orientation and the second orientation are nonparallel and nonorthogonal relative to a direction of flow of combustion exhaust gases.
15. A turbine blade, comprising:
a generally elongated blade having a leading edge, a trailing edge, a tip at a first end, a root coupled to the blade at a second end generally opposite the first end for supporting the blade and for coupling the blade to a disc;
a squealer tip coupled to the tip at the first end, wherein the squealer tip includes a plurality of abradable coating cutting tips that extend radially from the squealer tip toward a ring segment positioned radially outward from the generally elongated blade;
wherein the plurality of abradable coating cutting tips is formed into at least two rows of abradable coating cutting tips extending generally orthogonal to a flow of combustion exhaust gases between the squealer tip and the ring segment, and wherein a second row of abradable coating cutting tips is positioned downstream from a first row of abradable coating cutting tips and is offset orthogally to the flow of combustion exhaust gases relative to the first row of abradable coating cutting tips; and
wherein at least one of the abradable coating cutting tips has at least one cutting arris extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips.
16. The turbine blade of claim 15 , wherein at least one of the abradable coating cutting tips has at least three cutting arrises extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips, wherein a first cutting arris is positioned on an upstream side of the at least one of the abradable coating cutting tips, a second cutting arris extending from the squealer tip to the outermost tip of the at least one of the abradable coating cutting tips at a first intersection between the upstream side and a downstream side of the at least one of the abradable coating cutting tips, and a third cutting arris extending from the squealer tip to the outermost tip of the at least one of the abradable coating cutting tips at a second intersection between the upstream side and the downstream side of the at least one of the abradable coating cutting tips, wherein the second intersection is on an opposite side of the tip from the first side.
17. The turbine blade of claim 15 , wherein at least one of the plurality of abradable coating cutting tips has a pyramid shape.
18. The turbine blade of claim 15 , wherein at least one of the plurality of abradable coating cutting tips extends from the squealer tip a distance of at least 125 microns and less than 1,025 microns.
19. The turbine blade of claim 1 , wherein of the plurality of abradable coating cutting tips forms a knurled surface on the radially outer end of the squealer tip, wherein at least one of the plurality of abradable coating cutting tips is formed from a plurality of planar surfaces, wherein adjacent planar surfaces intersect to form a cutting arris.
20. The turbine blade of claim 19 , wherein the plurality of abradable coating cutting tips are separated at an outer surface of the squealer tip into rows by a plurality of linear lines positioned in a first orientation and a plurality of linear lines positioned in a second orientation, wherein the second orientation is orthogonal to the first orientation, and wherein the first orientation and the second orientation are nonparallel and nonorthogonal relative to a direction of flow of combustion exhaust gases.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/031,457 US20150078900A1 (en) | 2013-09-19 | 2013-09-19 | Turbine blade with airfoil tip having cutting tips |
CN201480051624.4A CN105531446A (en) | 2013-09-19 | 2014-08-20 | Turbine blade with airfoil tip having cutting tips |
JP2016515390A JP2016530421A (en) | 2013-09-19 | 2014-08-20 | Turbine blade having a blade tip with a cutting tip |
EP14758066.6A EP3047114A1 (en) | 2013-09-19 | 2014-08-20 | Turbine blade with airfoil tip having cutting tips |
PCT/US2014/051777 WO2015041787A1 (en) | 2013-09-19 | 2014-08-20 | Turbine blade with airfoil tip having cutting tips |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/031,457 US20150078900A1 (en) | 2013-09-19 | 2013-09-19 | Turbine blade with airfoil tip having cutting tips |
Publications (1)
Publication Number | Publication Date |
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US20150078900A1 true US20150078900A1 (en) | 2015-03-19 |
Family
ID=51429420
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/031,457 Abandoned US20150078900A1 (en) | 2013-09-19 | 2013-09-19 | Turbine blade with airfoil tip having cutting tips |
Country Status (5)
Country | Link |
---|---|
US (1) | US20150078900A1 (en) |
EP (1) | EP3047114A1 (en) |
JP (1) | JP2016530421A (en) |
CN (1) | CN105531446A (en) |
WO (1) | WO2015041787A1 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
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US9860392B2 (en) | 2015-06-05 | 2018-01-02 | Silicon Laboratories Inc. | Direct-current to alternating-current power conversion |
CN109356884A (en) * | 2018-12-21 | 2019-02-19 | 大连海事大学 | A kind of gas compressor moving blade with bionical top room |
US10995623B2 (en) | 2018-04-23 | 2021-05-04 | Rolls-Royce Corporation | Ceramic matrix composite turbine blade with abrasive tip |
US11346232B2 (en) | 2018-04-23 | 2022-05-31 | Rolls-Royce Corporation | Turbine blade with abradable tip |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3374539B1 (en) | 2015-11-10 | 2022-08-03 | Oerlikon Surface Solutions AG, Pfäffikon | Turbine clearance control coatings and method |
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US4652209A (en) * | 1985-09-13 | 1987-03-24 | Rockwell International Corporation | Knurled turbine tip seal |
US5017402A (en) * | 1988-12-21 | 1991-05-21 | United Technologies Corporation | Method of coating abradable seal assembly |
CA2048804A1 (en) * | 1990-11-01 | 1992-05-02 | Roger J. Perkins | Long life abrasive turbine blade tips |
DE4341216C2 (en) * | 1993-12-03 | 1997-01-16 | Mtu Muenchen Gmbh | Sealing component for gap or labyrinth seals and process for its manufacture |
DE4432998C1 (en) * | 1994-09-16 | 1996-04-04 | Mtu Muenchen Gmbh | Brush coating for metallic engine components and manufacturing process |
US6382913B1 (en) * | 2001-02-09 | 2002-05-07 | General Electric Company | Method and apparatus for reducing turbine blade tip region temperatures |
JP2002256808A (en) * | 2001-02-28 | 2002-09-11 | Mitsubishi Heavy Ind Ltd | Combustion engine, gas turbine and grinding layer |
JP2003148103A (en) * | 2001-11-09 | 2003-05-21 | Mitsubishi Heavy Ind Ltd | Turbine and its manufacturing method |
US6935836B2 (en) * | 2002-06-05 | 2005-08-30 | Allison Advanced Development Company | Compressor casing with passive tip clearance control and endwall ovalization control |
US6994514B2 (en) * | 2002-11-20 | 2006-02-07 | Mitsubishi Heavy Industries, Ltd. | Turbine blade and gas turbine |
US9133715B2 (en) * | 2006-09-20 | 2015-09-15 | United Technologies Corporation | Structural members in a pedestal array |
GB0822703D0 (en) * | 2008-12-15 | 2009-01-21 | Rolls Royce Plc | A component having an abrasive layer and a method of applying an abrasive layer on a component |
US8282346B2 (en) * | 2009-04-06 | 2012-10-09 | General Electric Company | Methods, systems and/or apparatus relating to seals for turbine engines |
EP2309098A1 (en) * | 2009-09-30 | 2011-04-13 | Siemens Aktiengesellschaft | Airfoil and corresponding guide vane, blade, gas turbine and turbomachine |
GB2475850A (en) * | 2009-12-02 | 2011-06-08 | Rolls Royce Plc | An Abrasive Layer and a Method Of Applying an Abrasive Layer on a Turbomachine Component |
US8690536B2 (en) * | 2010-09-28 | 2014-04-08 | Siemens Energy, Inc. | Turbine blade tip with vortex generators |
-
2013
- 2013-09-19 US US14/031,457 patent/US20150078900A1/en not_active Abandoned
-
2014
- 2014-08-20 WO PCT/US2014/051777 patent/WO2015041787A1/en active Application Filing
- 2014-08-20 EP EP14758066.6A patent/EP3047114A1/en not_active Withdrawn
- 2014-08-20 JP JP2016515390A patent/JP2016530421A/en active Pending
- 2014-08-20 CN CN201480051624.4A patent/CN105531446A/en active Pending
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9860392B2 (en) | 2015-06-05 | 2018-01-02 | Silicon Laboratories Inc. | Direct-current to alternating-current power conversion |
US10995623B2 (en) | 2018-04-23 | 2021-05-04 | Rolls-Royce Corporation | Ceramic matrix composite turbine blade with abrasive tip |
US11346232B2 (en) | 2018-04-23 | 2022-05-31 | Rolls-Royce Corporation | Turbine blade with abradable tip |
CN109356884A (en) * | 2018-12-21 | 2019-02-19 | 大连海事大学 | A kind of gas compressor moving blade with bionical top room |
Also Published As
Publication number | Publication date |
---|---|
CN105531446A (en) | 2016-04-27 |
EP3047114A1 (en) | 2016-07-27 |
WO2015041787A1 (en) | 2015-03-26 |
JP2016530421A (en) | 2016-09-29 |
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