US20170343113A1 - Thrust plate for butterfly valve - Google Patents
Thrust plate for butterfly valve Download PDFInfo
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- US20170343113A1 US20170343113A1 US15/678,317 US201715678317A US2017343113A1 US 20170343113 A1 US20170343113 A1 US 20170343113A1 US 201715678317 A US201715678317 A US 201715678317A US 2017343113 A1 US2017343113 A1 US 2017343113A1
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- United States
- Prior art keywords
- wear
- thrust plate
- resistant coating
- recess
- recited
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K1/00—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces
- F16K1/16—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members
- F16K1/18—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members with pivoted discs or flaps
- F16K1/22—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
- F16K1/224—Details of bearings for the axis of rotation
- F16K1/225—Details of bearings for the axis of rotation the axis of rotation having only one bearing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K1/00—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces
- F16K1/16—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members
- F16K1/18—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members with pivoted discs or flaps
- F16K1/22—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K27/00—Construction of housing; Use of materials therefor
- F16K27/02—Construction of housing; Use of materials therefor of lift valves
- F16K27/0209—Check valves or pivoted valves
- F16K27/0218—Butterfly valves
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49405—Valve or choke making
- Y10T29/49412—Valve or choke making with assembly, disassembly or composite article making
Definitions
- This disclosure relates to a butterfly valve having a wear-resistant coating.
- Butterfly valves are known and used to control air flow.
- a typical butterfly valve includes a housing that defines an air flow passage.
- a shaft is mounted in a housing and supports a butterfly disk.
- An actuator rotates the shaft to selectively open or close the butterfly disk to control the air flow through the passage in the housing.
- a thrust plate for a butterfly valve includes a thrust plate body that defines a recess that extends between a bottom thrust surface, side walls, and an open top.
- a nickel-based or cobalt-based wear-resistant coating is located on the bottom thrust surface. The wear-resistant coating is harder than the thrust plate body.
- the wear-resistant coating is a nickel-based alloy.
- the wear-resistant coating includes chromium boride.
- the wear-resistant coating includes chromium carbide.
- the thrust plate body is stainless steel.
- a ratio of a hardness of the wear-resistant coating to a hardness of the stainless steel is at least 2 . 3 .
- the recess defines a recess diameter (RD 1 ) and the wear-resistant coating defines an average coating thickness (CT), and ratio RD 1 /CT is between 33.2 and 56.67.
- the recess defines a recess depth (RD 2 ) and the wear-resistant coating defines an average coating thickness (CT), and a ratio RD 2 /CT is between 5 and 10 . 33 .
- the thrust plate body is free of the wear-resistant coating.
- the thrust plate body is a material selected from a group consisting of nickel-based alloy, cobalt-based alloy and steel, and the wear-resistant coating is a nickel-based alloy.
- a butterfly valve includes a valve housing that defines a flow passage there through, a shaft that extends in the valve housing, and gas a butterfly disk mounted thereon within the flow passage.
- a thrust plate includes a thrust plate body that defines a recess that receives an end of the shaft. The recess extends between a bottom thrust surface, side walls, and an open top. A wear-resistant coating is located on the bottom thrust surface.
- the wear-resistant coating consists essentially of 0.5-1.0 wt. % carbon, 12-18 wt. % chromium, 2.5-4.5 wt. % boron, 3.5-5.5 wt. % silicon, 3.5-5.5 wt. % iron, up to 0.2 wt. % cobalt, and a remainder of nickel
- the thrust plate body is stainless steel.
- a ratio of a hardness of the wear-resistant coating to a hardness of the stainless steel is at least 2.3.
- the recess defines a recess diameter (RD 1 ) and the wear-resistant coating defines an average coating thickness (CT), and ratio RD 1 /CT is between 33.2 and 56.67.
- the recess defines a recess depth (RD 2 ) and the wear-resistant coating defines an average coating thickness (CT), and a ratio RD 2 /CT is between 5 and 10.33.
- the thrust plate body is free of the wear-resistant coating.
- the flow passage defines a central axis, and a long axis of the shaft is non-perpendicular to the central axis.
- the recess defines a recess diameter (RD 1 ) and a recess depth (RD 2 ) and the wear-resistant coating defines an average coating thickness (CT) such that a ratio RD 1 /CT is between 33.2 and 56.67 and a ratio RD 2 /CT is between 5 and 10.33.
- CT average coating thickness
- a method of installing a thrust plate on a butterfly valve includes securing a thrust plate to a valve housing that defines a flow passage there through such that an end of a shaft, which extends within the valve housing and includes a butterfly disk mounted thereon, is received into a recess of the thrust plate body.
- the recess extends between a bottom thrust surface, side walls and an open top.
- the bottom thrust surface includes a wear-resistant coating thereon.
- FIG. 1 illustrates an example aircraft that includes an air management system.
- FIG. 2 is an isolated view of a thrust plate within a valve of the air management system.
- FIG. 3 is another view of the thrust plate of FIG. 2 .
- FIG. 4 is a cross-sectional view of the thrust plate shown in FIG. 3 .
- FIG. 1 illustrates selected portions of an example aircraft 10 that includes an air management system 12 mounted to a support 14 within the aircraft 10 .
- the example air management system 12 includes a conduit 16 that defines a flow passage 18 along a central axis A for air flow.
- a valve assembly 20 controls air flow through the flow passage 18 .
- the valve assembly 20 includes a valve housing 21 that defines at least a portion of the flow passage 18 .
- a butterfly disk 22 is mounted on a shaft 24 within the valve housing 21 , and an actuator 26 (e.g., a pneumatic actuator) is operatively connected to the shaft 24 to move the butterfly disk 22 about a long axis 28 of the shaft 24 .
- the shaft 24 includes an axial end 30 that is supported by a thrust plate 32 .
- the thrust plate 32 limits movement of the shaft along the long axis 28 .
- the air management system 12 is required to operate at elevated temperatures, such as 1200° F. (649° C.), and high vibration levels with little or no lubrication. Furthermore, the long axis 28 of the shaft 24 is non-perpendicular to the central axis A and thereby produces a thrust load along the long axis 28 (indicated at 34 ). As will be described, the example thrust plate 32 includes a wear-resistant coating 40 at the interface with the axial end 30 of the shaft 24 , to facilitate a reduction in friction and wear from the thrust load 34 that the shaft 24 exerts on the thrust plate 32 .
- the thrust plate 32 is formed from a thrust plate body 42 that defines a recess 44 therein.
- the recess 44 generally extends between a bottom thrust surface 46 , side walls 48 and an open top 50 .
- the axial end 30 of the shaft 24 is received into the recess 44 such that the axial end 30 contacts the bottom thrust surface 46 .
- the thrust plate body 42 includes a wear-resistant coating 40 on the bottom thrust surface 46 to resist wear between the thrust plate body 42 and the shaft 24 from the thrust load 34 produced during operation of the valve assembly 20 .
- the recess 44 defines a recess diameter (RD 1 ) and a recess depth (RD 2 ).
- the recess depth extends between the bottom thrust surface 46 and a plane that is defined by a ledge or step 51 in the recess 44 .
- the recess depth is taken from the lower portion of the step 51 at the location where the recess 44 narrows to the recess diameter.
- the wear-resistant coating 40 also defines an average coating thickness (CT).
- CT average coating thickness
- the average coating thickness may be an average of thicknesses taken at selected locations across the wear-resistant coating 40 .
- the recess diameter (RD 1 ) is 0.830-0.850 inches and may nominally be 0.840 inches.
- the recess depth (RD 2 ) is 0.125-0.155 inches and may nominally be 0.140 inches.
- the coating thickness (CT) is 0.015-0.025 inches and may nominally be 0.020 inches.
- the thrust plate 32 and wear-resistant coating 40 are designed with a ratio of RD 1 /CT that is between 33.2 and 56.67. In a further embodiment, the thrust plate 32 and wear-resistant coating 40 are also designed with a ratio of RD 2 /CT that is between 5 and 10.33. The selected ratios ensure that the wear-resistant coating 40 has a sufficient thickness to provide wear-resistance for a given recess size and also ensure that the wear-resistant coating 40 provides the proper axial positioning of the shaft 24 .
- the wear-resistant coating 40 is designed to be harder than the material of the thrust plate body 42 to thereby provide the wear-resistance.
- the material of the thrust plate body 42 may be an austenitic or precipitation hardened stainless steel.
- the material of the thrust plate body 42 may be a nickel-based alloy, a cobalt-based alloy or steel.
- the nickel-based alloy may be Inconel® 625 or 718, the cobalt-based alloy may be Haynes® 25, Stellite® 31 or Stellite® 60.
- the element that is the base element of the alloy refers to that element being present in a greater amount than any other element in the composition.
- the material of the wear-resistant coating 40 is designed to protect the thrust plate body 42 .
- the wear-resistant coating 40 is a nickel-based alloy or a cobalt-based alloy that is harder than the material of the thrust plate body 42 .
- the nickel-based alloy may have a composition that essentially includes 0.5-1.0 wt. % carbon, 12-18 wt. % chromium, 2.5-4.5 wt. % boron, 3.5-5.5 wt. % silicon, 3.5-5.5 wt. % iron, up to 0.2 wt. % cobalt, and a remainder of nickel.
- the alloys may include impurities that do not affect the properties of the material or elements that are unmeasured or undetectable in the material.
- the nickel-based alloy of the wear-resistant coating 40 may include hard compounds or phases that contribute to the high hardness of the wear-resistant coating 40 .
- the hard compounds or phases may include chromium boride, chromium carbide, or both.
- the wear-resistant coating 40 may additionally include silicides.
- the borides, carbides, and/or silicides may be formed between the elements of the composition of the wear-resistant coating 40 .
- the flow passage 18 of the valve assembly 20 defines a diameter (D p ) ( FIG. 1 ) and the shaft 24 contacts the wear-resistant coating 40 over an interface area (CA) ( FIG. 4 ).
- a ratio D p /CA determines the amount of thrust load 34 on the bottom thrust surface 46 of the thrust plate 32 .
- the ratio D p /CA is between 8 and 12.
- the relative hardness of the wear-resistant coating 40 in comparison to the hardness of the material of the thrust plate body 42 is designed to provide a desired level of wear-resistance.
- a ratio of the hardness of the wear-resistant coating 40 to the hardness of the material of the thrust plate body 42 is at least 2.3.
- the hardness of the wear-resistant coating 40 may be at least 55 HRC and the hardness of the material of the thrust plate body 42 may be a maximum of 23 HRC.
- the wear-resistant coating 40 thereby provides a sufficient level of wear-resistance with regard to the thrust load 34 that is expected from the given ratio D p /CA.
- the wear-resistant coating 40 resists wear such that during the operation of the valve assembly 20 , the shaft 24 and butterfly disk 22 maintain a concentric position within the flow passage 18 .
- the shaft 24 and butterfly disk 22 therefore do not shift position due to thrust plate 32 wear that could otherwise lead to binding and hindering of valve operation. That is, the absence of the wear-resistant coating 40 may otherwise lead to wear of the shaft 24 and/or of the bottom thrust surface 46 under the given thrust load 34 such that the shaft 24 and butterfly disk 22 shift in position and potentially hinder the operation of the valve.
- the axial end 30 of the shaft 24 may include a plug 52 that is mounted in the axial end 30 for contact with the wear-resistant coating 40 .
- the plug 52 may be formed of a hard material that resists wear.
- the thrust plate 32 also includes a plurality of mounts 52 for securing the thrust plate 32 to the valve housing 21 .
- the thrust plate 32 includes three such mounts 52 that are uniformly spaced around the periphery of the thrust plate 32 .
- each of the mounts 52 includes an opening 54 therein for receiving a bolt 56 ( FIG. 1 ) to secure the thrust plate 32 to the valve housing 21 .
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Lift Valve (AREA)
Abstract
Description
- This application is a continuation U.S. application Ser. No. 13/007,850 filed on Jan. 17, 2011.
- This disclosure relates to a butterfly valve having a wear-resistant coating.
- Butterfly valves are known and used to control air flow. A typical butterfly valve includes a housing that defines an air flow passage. A shaft is mounted in a housing and supports a butterfly disk. An actuator rotates the shaft to selectively open or close the butterfly disk to control the air flow through the passage in the housing.
- A thrust plate for a butterfly valve according to an example of the present disclosure includes a thrust plate body that defines a recess that extends between a bottom thrust surface, side walls, and an open top. A nickel-based or cobalt-based wear-resistant coating is located on the bottom thrust surface. The wear-resistant coating is harder than the thrust plate body.
- In a further embodiment of any of the foregoing embodiments, the wear-resistant coating is a nickel-based alloy.
- In a further embodiment of any of the foregoing embodiments, the wear-resistant coating includes chromium boride.
- In a further embodiment of any of the foregoing embodiments, the wear-resistant coating includes chromium carbide.
- In a further embodiment of any of the foregoing embodiments, the thrust plate body is stainless steel.
- In a further embodiment of any of the foregoing embodiments, a ratio of a hardness of the wear-resistant coating to a hardness of the stainless steel is at least 2.3.
- In a further embodiment of any of the foregoing embodiments, the recess defines a recess diameter (RD1) and the wear-resistant coating defines an average coating thickness (CT), and ratio RD1/CT is between 33.2 and 56.67.
- In a further embodiment of any of the foregoing embodiments, the recess defines a recess depth (RD2) and the wear-resistant coating defines an average coating thickness (CT), and a ratio RD2/CT is between 5 and 10.33.
- In a further embodiment of any of the foregoing embodiments, the thrust plate body, with the exception of the bottom thrust surface, is free of the wear-resistant coating.
- In a further embodiment of any of the foregoing embodiments, the thrust plate body is a material selected from a group consisting of nickel-based alloy, cobalt-based alloy and steel, and the wear-resistant coating is a nickel-based alloy.
- A butterfly valve according to an example of the present disclosure includes a valve housing that defines a flow passage there through, a shaft that extends in the valve housing, and gas a butterfly disk mounted thereon within the flow passage. A thrust plate includes a thrust plate body that defines a recess that receives an end of the shaft. The recess extends between a bottom thrust surface, side walls, and an open top. A wear-resistant coating is located on the bottom thrust surface.
- In a further embodiment of any of the foregoing embodiments, the wear-resistant coating consists essentially of 0.5-1.0 wt. % carbon, 12-18 wt. % chromium, 2.5-4.5 wt. % boron, 3.5-5.5 wt. % silicon, 3.5-5.5 wt. % iron, up to 0.2 wt. % cobalt, and a remainder of nickel
- In a further embodiment of any of the foregoing embodiments, the thrust plate body is stainless steel.
- In a further embodiment of any of the foregoing embodiments, a ratio of a hardness of the wear-resistant coating to a hardness of the stainless steel is at least 2.3.
- In a further embodiment of any of the foregoing embodiments, the recess defines a recess diameter (RD1) and the wear-resistant coating defines an average coating thickness (CT), and ratio RD1/CT is between 33.2 and 56.67.
- In a further embodiment of any of the foregoing embodiments, the recess defines a recess depth (RD2) and the wear-resistant coating defines an average coating thickness (CT), and a ratio RD2/CT is between 5 and 10.33.
- In a further embodiment of any of the foregoing embodiments, the thrust plate body, with the exception of the bottom thrust surface, is free of the wear-resistant coating.
- In a further embodiment of any of the foregoing embodiments, the flow passage defines a central axis, and a long axis of the shaft is non-perpendicular to the central axis.
- In a further embodiment of any of the foregoing embodiments, the recess defines a recess diameter (RD1) and a recess depth (RD2) and the wear-resistant coating defines an average coating thickness (CT) such that a ratio RD1/CT is between 33.2 and 56.67 and a ratio RD2/CT is between 5 and 10.33.
- A method of installing a thrust plate on a butterfly valve according to an example of the present disclosure includes securing a thrust plate to a valve housing that defines a flow passage there through such that an end of a shaft, which extends within the valve housing and includes a butterfly disk mounted thereon, is received into a recess of the thrust plate body. The recess extends between a bottom thrust surface, side walls and an open top. The bottom thrust surface includes a wear-resistant coating thereon.
- The various features and advantages of the disclosed examples will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows.
-
FIG. 1 illustrates an example aircraft that includes an air management system. -
FIG. 2 is an isolated view of a thrust plate within a valve of the air management system. -
FIG. 3 is another view of the thrust plate ofFIG. 2 . -
FIG. 4 is a cross-sectional view of the thrust plate shown inFIG. 3 . -
FIG. 1 illustrates selected portions of anexample aircraft 10 that includes anair management system 12 mounted to asupport 14 within theaircraft 10. The exampleair management system 12 includes aconduit 16 that defines aflow passage 18 along a central axis A for air flow. - A
valve assembly 20 controls air flow through theflow passage 18. Thevalve assembly 20 includes avalve housing 21 that defines at least a portion of theflow passage 18. Abutterfly disk 22 is mounted on ashaft 24 within thevalve housing 21, and an actuator 26 (e.g., a pneumatic actuator) is operatively connected to theshaft 24 to move thebutterfly disk 22 about along axis 28 of theshaft 24. Theshaft 24 includes anaxial end 30 that is supported by athrust plate 32. Thethrust plate 32 limits movement of the shaft along thelong axis 28. - The
air management system 12 is required to operate at elevated temperatures, such as 1200° F. (649° C.), and high vibration levels with little or no lubrication. Furthermore, thelong axis 28 of theshaft 24 is non-perpendicular to the central axis A and thereby produces a thrust load along the long axis 28 (indicated at 34). As will be described, theexample thrust plate 32 includes a wear-resistant coating 40 at the interface with theaxial end 30 of theshaft 24, to facilitate a reduction in friction and wear from thethrust load 34 that theshaft 24 exerts on thethrust plate 32. - Referring to
FIGS. 2-4 , thethrust plate 32 is formed from athrust plate body 42 that defines arecess 44 therein. Therecess 44 generally extends between abottom thrust surface 46,side walls 48 and anopen top 50. As shown inFIG. 1 , theaxial end 30 of theshaft 24 is received into therecess 44 such that theaxial end 30 contacts thebottom thrust surface 46. In that regard, thethrust plate body 42 includes a wear-resistant coating 40 on thebottom thrust surface 46 to resist wear between thethrust plate body 42 and theshaft 24 from thethrust load 34 produced during operation of thevalve assembly 20. - In the example shown in
FIG. 4 , therecess 44 defines a recess diameter (RD1) and a recess depth (RD2). The recess depth extends between thebottom thrust surface 46 and a plane that is defined by a ledge or step 51 in therecess 44. In this example, the recess depth is taken from the lower portion of thestep 51 at the location where therecess 44 narrows to the recess diameter. - The wear-
resistant coating 40 also defines an average coating thickness (CT). For instance, the average coating thickness may be an average of thicknesses taken at selected locations across the wear-resistant coating 40. - In embodiments, the recess diameter (RD1) is 0.830-0.850 inches and may nominally be 0.840 inches. The recess depth (RD2) is 0.125-0.155 inches and may nominally be 0.140 inches. The coating thickness (CT) is 0.015-0.025 inches and may nominally be 0.020 inches.
- In embodiments, the
thrust plate 32 and wear-resistant coating 40 are designed with a ratio of RD1/CT that is between 33.2 and 56.67. In a further embodiment, thethrust plate 32 and wear-resistant coating 40 are also designed with a ratio of RD2/CT that is between 5 and 10.33. The selected ratios ensure that the wear-resistant coating 40 has a sufficient thickness to provide wear-resistance for a given recess size and also ensure that the wear-resistant coating 40 provides the proper axial positioning of theshaft 24. - The wear-
resistant coating 40 is designed to be harder than the material of thethrust plate body 42 to thereby provide the wear-resistance. As an example, the material of thethrust plate body 42 may be an austenitic or precipitation hardened stainless steel. In other embodiments, the material of thethrust plate body 42 may be a nickel-based alloy, a cobalt-based alloy or steel. The nickel-based alloy may be Inconel® 625 or 718, the cobalt-based alloy may be Haynes® 25, Stellite® 31 or Stellite® 60. The element that is the base element of the alloy refers to that element being present in a greater amount than any other element in the composition. - The material of the wear-
resistant coating 40 is designed to protect thethrust plate body 42. In embodiments, the wear-resistant coating 40 is a nickel-based alloy or a cobalt-based alloy that is harder than the material of thethrust plate body 42. As an example, the nickel-based alloy may have a composition that essentially includes 0.5-1.0 wt. % carbon, 12-18 wt. % chromium, 2.5-4.5 wt. % boron, 3.5-5.5 wt. % silicon, 3.5-5.5 wt. % iron, up to 0.2 wt. % cobalt, and a remainder of nickel. The alloys may include impurities that do not affect the properties of the material or elements that are unmeasured or undetectable in the material. - The nickel-based alloy of the wear-
resistant coating 40 may include hard compounds or phases that contribute to the high hardness of the wear-resistant coating 40. For instance, the hard compounds or phases may include chromium boride, chromium carbide, or both. The wear-resistant coating 40 may additionally include silicides. The borides, carbides, and/or silicides may be formed between the elements of the composition of the wear-resistant coating 40. - The
flow passage 18 of thevalve assembly 20 defines a diameter (Dp) (FIG. 1 ) and theshaft 24 contacts the wear-resistant coating 40 over an interface area (CA) (FIG. 4 ). A ratio Dp/CA determines the amount ofthrust load 34 on thebottom thrust surface 46 of thethrust plate 32. In embodiments, the ratio Dp/CA is between 8 and 12. - The relative hardness of the wear-
resistant coating 40 in comparison to the hardness of the material of thethrust plate body 42 is designed to provide a desired level of wear-resistance. For instance, a ratio of the hardness of the wear-resistant coating 40 to the hardness of the material of thethrust plate body 42 is at least 2.3. In a further example, the hardness of the wear-resistant coating 40 may be at least 55 HRC and the hardness of the material of thethrust plate body 42 may be a maximum of 23 HRC. The wear-resistant coating 40 thereby provides a sufficient level of wear-resistance with regard to thethrust load 34 that is expected from the given ratio Dp/CA. - The wear-
resistant coating 40 resists wear such that during the operation of thevalve assembly 20, theshaft 24 andbutterfly disk 22 maintain a concentric position within theflow passage 18. Theshaft 24 andbutterfly disk 22 therefore do not shift position due to thrustplate 32 wear that could otherwise lead to binding and hindering of valve operation. That is, the absence of the wear-resistant coating 40 may otherwise lead to wear of theshaft 24 and/or of thebottom thrust surface 46 under the giventhrust load 34 such that theshaft 24 andbutterfly disk 22 shift in position and potentially hinder the operation of the valve. - Optionally, as shown in
FIG. 1 , theaxial end 30 of theshaft 24 may include aplug 52 that is mounted in theaxial end 30 for contact with the wear-resistant coating 40. Theplug 52 may be formed of a hard material that resists wear. - In the illustrated example, the
thrust plate 32 also includes a plurality ofmounts 52 for securing thethrust plate 32 to thevalve housing 21. In embodiments, thethrust plate 32 includes threesuch mounts 52 that are uniformly spaced around the periphery of thethrust plate 32. As an example, each of themounts 52 includes anopening 54 therein for receiving a bolt 56 (FIG. 1 ) to secure thethrust plate 32 to thevalve housing 21. - Although a combination of features is shown in the illustrated examples, not all of them need to be combined to realize the benefits of various embodiments of this disclosure. In other words, a system designed according to an embodiment of this disclosure will not necessarily include all of the features shown in any one of the Figures or all of the portions schematically shown in the Figures. Moreover, selected features of one example embodiment may be combined with selected features of other example embodiments.
- The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from the essence of this disclosure. The scope of legal protection given to this disclosure can only be determined by studying the following claims.
Claims (20)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US15/678,317 US20170343113A1 (en) | 2011-01-17 | 2017-08-16 | Thrust plate for butterfly valve |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US13/007,850 US9816619B2 (en) | 2011-01-17 | 2011-01-17 | Thrust plate for butterfly valve |
US15/678,317 US20170343113A1 (en) | 2011-01-17 | 2017-08-16 | Thrust plate for butterfly valve |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US13/007,850 Continuation US9816619B2 (en) | 2011-01-17 | 2011-01-17 | Thrust plate for butterfly valve |
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US20170343113A1 true US20170343113A1 (en) | 2017-11-30 |
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Application Number | Title | Priority Date | Filing Date |
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US13/007,850 Active 2035-05-30 US9816619B2 (en) | 2011-01-17 | 2011-01-17 | Thrust plate for butterfly valve |
US15/678,317 Abandoned US20170343113A1 (en) | 2011-01-17 | 2017-08-16 | Thrust plate for butterfly valve |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
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US13/007,850 Active 2035-05-30 US9816619B2 (en) | 2011-01-17 | 2011-01-17 | Thrust plate for butterfly valve |
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US (2) | US9816619B2 (en) |
CN (1) | CN102588619B (en) |
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Also Published As
Publication number | Publication date |
---|---|
US9816619B2 (en) | 2017-11-14 |
US20120181469A1 (en) | 2012-07-19 |
CN102588619B (en) | 2017-09-05 |
CN102588619A (en) | 2012-07-18 |
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