CN104121228A - Turbine nozzle piece parts with HVOC coatings - Google Patents

Turbine nozzle piece parts with HVOC coatings Download PDF

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Publication number
CN104121228A
CN104121228A CN201410125935.2A CN201410125935A CN104121228A CN 104121228 A CN104121228 A CN 104121228A CN 201410125935 A CN201410125935 A CN 201410125935A CN 104121228 A CN104121228 A CN 104121228A
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CN
China
Prior art keywords
nozzle
turbine
flow region
blades
working fluid
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.)
Pending
Application number
CN201410125935.2A
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Chinese (zh)
Inventor
C.M.比尔斯
D.A.科尔森
S.E.罗森
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Hamilton Sundstrand Corp
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Hamilton Sundstrand Corp
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Publication of CN104121228A publication Critical patent/CN104121228A/en
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • F02C1/02—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being an unheated pressurised gas
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A nozzle for an air cycle machine. The nozzle has a disk section having a central axis. The nozzle also includes a plurality of blades which extend a blade height H from a bladed face of the disk section. The plurality of blades are arranged radially about the disk section. The nozzle has a throat width W defined between each radially adjacent pair of the plurality of turbine blades. The nozzle includes a coating substantially encapsulating the disk section and the plurality of blades, wherein the coating contains more than 91 percent tungsten carbide by volume.

Description

There are the parts of the turbine nozzle part of HVOF coating
Background technique
The present invention relates to air cycle machine (ACM), as the type of the environmental control system for aircraft.Especially, the present invention relates to novel size and the coating for the turbine nozzle of ACM.
ACM is used in pressurized air in compressor section.Pressurized air is disposed to downstream heat exchanger and is caused further turbine.Turbine extracts energy with drive compression machine from the air expanding.The air output that is derived from turbine can be used as vehicle, as the air supply of aircraft cabin.
ACM has three-wheel or four-wheel configuration conventionally.In three-wheel ACM, the compressor that turbine drives is rotated on common axle and fan.In four-wheel ACM, two turbine parts drive compressor and the fan on common axle.
Air-flow must be directed to fan part to reach compressor section, to be drawn towards heat exchanger, to be directed to turbine and to be drawn ACM from final turbine stage from heat exchanger away from compressor section.In at least some in these shift, ideal state is radially to guide air about the medial axis of ACM.In order to realize this object, swivel nozzle can be used for generating radially influent stream and/or goes out stream.
Conventionally, ideal state is assembly, avoids as nozzle etc. comprises protection assembly the coating of damaging.For example, use pinking rifle to apply and applied tungsten carbide coating.
Plasma spray technology is well known in the art and is usually used in applying thick coating to change the surface property of assembly.The example of known plasma spray technology comprises that pinking rifle applies, and wherein high-pressure shocking wave is by air-flow and the discharge of material breaks is deposited.Another known method of thermal spraying is high-velocity oxy-fuel (HVOF), wherein fuel continuous burning, thus allow the Continuous Flow of material to deposit.
Summary of the invention
In one embodiment, disclose a kind of nozzle for air cycle machine, it comprises the integrated disc portions with medial axis.Nozzle also comprises blade, and it is from vaned extended blade height H of filling of integrated disc portions.Blade is radially arranged about integrated disc portions.Each radially adjoinings of multiple turbine blades between be limited with throat's width W.Coating encapsulates integrated disc portions and multiple blade substantially, and its floating coat contains the Tungsten carbite that is greater than 91 volume %.
In another embodiment, disclose a kind of nozzle for air cycle machine, it also comprises the integrated disc portions with medial axis.Nozzle also comprises blade, and it is from vaned extended blade height H of filling of integrated disc portions.Blade is radially arranged about integrated disc portions.Each radially adjoinings of multiple turbine blades between be limited with throat's width W.The coating of basic encapsulation integrated disc portions and multiple blades has the thickness of 50.8 μ m-101.6 μ m.
In the 3rd embodiment, a kind of nozzle for air cycle machine is disclosed, it also comprises the integrated disc portions with medial axis.Nozzle also comprises blade, and it is from vaned extended blade height H of filling of integrated disc portions.Blade is radially arranged about integrated disc portions.Each radially adjoinings of multiple turbine blades between be limited with throat's width W.The coating of basic encapsulation integrated disc portions and multiple blades comprises metal alloy, and it has the bonding strength that is greater than 10,000psi.
Brief description of the drawings
Fig. 1 is the sectional view of four-wheel air cycle machine.
Fig. 2 is the planimetric map of the turbine nozzle in the four-wheel air cycle machine shown in Fig. 1.
Fig. 3 is the side view of the turbine nozzle shown in Fig. 2.
Fig. 4 is the planimetric map of a part for the turbine nozzle shown in Fig. 2, and it shows the size of nozzle.
Fig. 5 is the planimetric map of the turbine nozzle in the four-wheel air cycle machine shown in Fig. 1.
Fig. 6 is the side view of the turbine nozzle shown in Fig. 5.
Fig. 7 is the planimetric map of a part for the turbine nozzle shown in Fig. 5, and it shows the size of nozzle.
Fig. 8 is the sectional view of three-wheel air cycle machine.
Fig. 9 is the planimetric map of the turbine nozzle in the three-wheel air cycle machine shown in Fig. 8.
Figure 10 is the side view of the turbine nozzle shown in Fig. 9.
Figure 11 is the planimetric map of a part for the turbine nozzle shown in Fig. 9, and it shows the size of nozzle.
Figure 12 is the planimetric map of the turbine nozzle in the three-wheel air cycle machine shown in Fig. 8.
Figure 13 is the side view of the turbine nozzle shown in Figure 12.
Figure 14 is the planimetric map of a part for the turbine nozzle shown in Figure 12, and it shows the size of nozzle.
Embodiment
Fig. 1 is the sectional view of air cycle machine (ACM) 2.ACM2 4 takes turns ACM, contains fan part 4, compressor section 6, the first turbine part 8 and the second turbine part 10, and it is all connected to axle 12.Axle 12 rotates about medial axis 14.
Fan part 4 comprises fan entrance 16 and fan outlet 18.Fan entrance 16 is from another source, as the opening in the ACM2 of ram intake reception working fluid.Fan outlet 18 allows working fluid to flee from fan part 4.Fan blade 20 can be used for working fluid suction fan part 4.
Compressor section 6 comprises suction port of compressor 22, compressor outlet 24, compressor nozzle 26 and compressor blade 27.The to be compressed working fluid of this aperture reception sources from another source, for limiting the pipeline in aperture, wherein passed through in suction port of compressor 22.Compressor outlet 24 allows working fluid to be directed to other system after compressed.Compressor nozzle 26 is the nozzle segment of the working fluid rotation by compressor section 6.Compressor nozzle 26 causes compressor outlet 24 by working fluid from suction port of compressor 22 through compressor blade 27.Compressor nozzle 26 is for radially going out circulation.
The first turbine part 8 comprises first order turbine inlet 28, first order turbine outlet 30, first order turbine nozzle 32 and the first turbine blade 33.First order turbine inlet 28 is for limiting the pipeline in aperture, and before wherein expanding in the first turbine part 8, working fluid is by this aperture.First order turbine outlet 30 is for limiting the pipeline in aperture, and wherein working fluid (having expanded) leaves the first turbine part 8 by this aperture.First order turbine nozzle 32 is the nozzle segment of the working fluid rotation by the first turbine part 8.First order turbine nozzle 32 cooperates to extract energy from the working fluid by it with first order turbine blade 37, thereby drives the first turbine part 8 and appended assembly, comprises the rotation of axle 12, fan part 4 and compressor section 6.First order turbine nozzle 32 is influent stream rotor radially.
The first turbine part 10 comprises first order turbine inlet 34, first order turbine outlet 36, first order turbine nozzle 38 and the first turbine blade 39.First order turbine inlet 34 is for limiting the pipeline in aperture, and before wherein expanding in the first turbine part 10, working fluid is by this aperture.First order turbine outlet 36 is for limiting the pipeline in aperture, and wherein working fluid (having expanded) leaves the first turbine part 10 by this aperture.Second level turbine nozzle 38 is for to cooperate extracting energy from the working fluid by it with second level turbine blade 39, thus the nozzle segment of the rotation of driving the second turbine part 10 and appended assembly (comprising axle 12, fan part 4 and compressor section 6).Particularly, second level turbine nozzle 38 is influent stream rotor radially.Working fluid flow to chamber 35 from second level turbine inlet 34, and this follows second level turbine nozzle 38 and produces.Then, working fluid passes through (Fig. 5-7) between nozzle vane 50 and 52.Turbine nozzle 38 is for fixing, and nozzle vane carries out water conservancy diversion and enters in the best way turbine rotor.This flows and makes turbine blade 39 rotation rotatingshafts 12.
Axle 12 is bar, and as titanium pull bar, it is for connecting other assemblies of ACM2.The axis that medial axis 14 can arrange about it for other assemblies.
Fan part 4 is connected to compressor section 6.Especially, fan outlet 18 is attached to suction port of compressor 22.Suck working fluid and discharge working fluid by fan outlet 18 by fan entrance 16 through fan blade 20.Be directed to suction port of compressor 22 to compress from fan outlet 18 working fluid out compressor section 6.Similarly, compressor section 6 and the first turbine part 8 are connected.Be directed to first order turbine inlet 28 from compressor outlet 24 working fluid out.
Similarly, the first turbine part 8 is attached to the second turbine part 10.Be directed to second level turbine inlet 34 from first order turbine outlet 30 working fluid out.By this way, working fluid passes through ACM2: first pass through fan entrance 16, follow by fan outlet 18, suction port of compressor 22, compressor outlet 24, first order turbine inlet 28, first order turbine outlet 30, second level turbine inlet 34 and second level turbine outlet 38.Between those ranks shown in Fig. 1, can there is extra rank.For example, heat exchanger (not shown) is often between compressor section 6 and the first turbine part 8.
Also warp beam 12 and connected with each other of each in fan part 4, compressor section 6, the first turbine part 8 and the second turbine part 10.Axle 12 extends along medial axis 14 and is at least connected to compressor nozzle 26, first order turbine nozzle 32 and second level turbine nozzle 38.Fan blade 20 also can be connected to axle 12.
In the time that working fluid passes through ACM2, first in compressor section 6, compress, in the first turbine part 8 and the second turbine part 10, expand subsequently.Conventionally, in heat exchanger (not shown), also working fluid is heated or cooling, when working fluid between compressor section 6 and the first turbine part 8 by time, it determines route by heat exchanger.The first turbine part 8 and the second turbine part 10 are extracted energy from working fluid, thereby about medial axis 14 rotatingshafts 12.
The adjustable working fluid by ACM2 is for being provided by gas turbine engine in the central chamber of vehicle of power.By compression, heating and expansion working fluid, can be adjusted to required temperature, pressure and/or relative humidity.But because compressor nozzle 26, first order turbine nozzle 32 and second level turbine nozzle 38 carry out fast rotational with respect to working fluid runner, therefore these parts need often to change.
Fig. 2 is the planimetric map of the first order turbine nozzle 32 that arranges about medial axis 14.First order turbine nozzle 32 comprises 19 whole laminas 40 that arrange along disk 42 surfaces.Whole lamina 40 and disk 42 are by durable material, as made in steel, aluminium or titanium.First order turbine nozzle 32 scribbles Tungsten carbite.Use HVOF be applied to the tungsten carbide coating on first order turbine nozzle 32, its allow improve hardness and with respect to other materials, as the Tungsten carbite of the higher percent of cobalt.With traditional painting method, as deposition-gun, spraying is compared, and HVOF spraying has also caused the variable reduction of coating thickness.
Disk 42 is about medial axis 14 radial symmetric.Whole lamina 40 is equidistantly spaced apart each other along the girth of disk 42.Each in whole lamina 40 is all radially equidistantly away from medial axis 14.
The high value assembly of first order turbine nozzle 32 for changing more continually.Owing to contacting with abrasive particle, can cause the damage to first order turbine nozzle 32.Therefore, the coating of high-strength durable can improve the life-span of first order turbine nozzle 32.
Fig. 3 is the side view of first order turbine nozzle 32.First order turbine nozzle 32 contains whole lamina 40 and disk 42, as described with reference to Figure 2.
Fig. 3 shows the thickness of first order turbine nozzle 32.Especially, first order turbine nozzle 32 comprises blade height H32.Blade height H32 is disk 42 and adjacent component, as the head room amount between cover (not shown).Blade height H32 shown in Fig. 3 is 0.686cm (0.270 inch).In certain embodiments, the variation of blade height H32 can be up to 0.01cm (0.005 inch).But in order to make the working fluid of aequum by the first turbine part 8 (Fig. 1), the blade height H32 of 0.686cm is desirable.
Fig. 4 is the enlarged view of a part for first order turbine nozzle 32.Shown the whole lamina 40 of being located on disk 42 in the part shown in Fig. 4.
Fig. 4 shows the various concrete size of first order turbine nozzle 32.Nozzle passage width W 32 is the distance between each whole lamina 40 and the whole lamina 40 of radially adjoining.In fact throat's width that, nozzle passage width W 32 can be passed through for control air.Nozzle passage width W 32 is 0.340cm (0.134 inch), but its deviation can be up to 0.013cm (0.005 inch).Flow region A32 is the region that working fluid can be flowed through.Flow region A32 assembles between blade until it reaches the throat of first order turbine nozzle 32, and has the surface area of nozzle height H32 × nozzle passage width W 32.Due to machining tolerance, the variation of flow region A32 can be up to 5%.Flow region A32 is approximately 4.432cm 2(0.687 square inch).
Optimize nozzle passage width W 32 to guarantee to be derived from suitable the flowing and energy extraction of first order turbine nozzle 32.Increase or reduce nozzle passage width W 32 too large or too little by causing by flowing of first order turbine nozzle 32.Similarly, optimize flow region A32 and transmitted the working fluid of suitable quantity to guarantee first order turbine nozzle 32.Larger flow region A32 will cause the working fluid by first order turbine nozzle 32 too many, and less flow region A32 will cause working fluid very little.
Fig. 5 is the planimetric map of the second level turbine nozzle 38 that arranges about medial axis 14.Second level turbine nozzle 38 comprises 50 and 17 splitterr vanes 52 of 17 whole laminas that arrange along disk 54 surfaces.Whole lamina 50, splitterr vanes 52 and disk 54 are by durable material, as made in steel, aluminium or titanium.Second level turbine nozzle 38 scribbles Tungsten carbite.Use high-velocity oxy-fuel (HVOF) spraying to be applied to tungsten carbide coating on second level turbine nozzle 38, it allows the hardness that improves and with respect to other materials, as the Tungsten carbite of the higher percent of cobalt.
Disk 54 is about medial axis 14 radial symmetric.Whole lamina 50 and splitterr vanes 52 are along the girth of disk 54 fourchette and spaced apart equidistantly each other.Therefore, each in whole lamina 50 is all between two adjacent splitterr vanes 52, and each in splitterr vanes 52 is all between two adjacent whole laminas 50.Each in each in splitterr vanes 52 and whole lamina 50 is all radially equidistantly away from medial axis 14.
The high value assembly of second level turbine nozzle 38 for changing more continually.Owing to thering is abrasive particle in the high velocity air guiding at second level turbine nozzle 38, may cause the damage to second level turbine nozzle 38.Therefore the coating that, the height on second level turbine nozzle 38 is durable can improve its life-span.
The HVOF coating of second level turbine nozzle causes physical features uniquely, and it can not be by using traditional paint-on technique, as deposition-gun applies and obtains.For example, HVOF coating can allow the exceedance of levels 91% of Tungsten carbite.In addition, HVOF coating provides the surface hardness that exceedes 10,000psi.In addition,, compared with applying with pinking rifle, HVOF coating reduces the variability of the thickness of cover coat.
Fig. 6 is the side view of second level turbine nozzle 38.Second level turbine nozzle 38 contains whole lamina 50, splitterr vanes 52 and disk 54, as described in reference to Fig. 5.
Fig. 6 shows the thickness of second level turbine nozzle 38.Especially, second level turbine nozzle 38 comprises blade height H38.Blade height H38 is disk 54 and adjacent component, as the head room amount between cover (not shown).Blade height H38 shown in Fig. 6 is 0.940cm (0.370 inch).In certain embodiments, the variation of blade height H38 can be up to 0.01cm (0.005 inch).But in order to make the working fluid of aequum by the second turbine part 10 (Fig. 1), the blade height H38 of 0.940cm is desirable.
Fig. 7 is the enlarged view of a part for second level turbine nozzle 38.Whole lamina 50 and the splitterr vanes 52 be located on disk 54 have been shown at the enlarged portion shown in Fig. 7.
Fig. 7 shows the various concrete size of second level turbine nozzle 38.Nozzle passage width W 38 is the distance between each whole lamina 50 and adjacent splitterr vanes 52.In fact throat's width that, nozzle passage width W 38 can be passed through for control air.Nozzle passage width W 38 is 0.222cm (0.0875 inch), but its deviation can be up to 0.013cm (0.005 inch).Flow region A38 is the region that working fluid can be flowed through.Flow region A38 is and the orthogonal total cross-section area in disk in blade-side 54 surfaces is being housed, and it is not covered by whole lamina 50 and splitterr vanes 52, and working fluid this flow region A38 that flows through.The part of the flow region A38 identifying in Fig. 7 is the flow region A between a whole lamina 50 and splitterr vanes 52.In a word, the flow region A38 on the whole surface of second level turbine nozzle 38 is 7.103cm 2(1.101 square inches).Minute differences due to processing and/or in applying, this value can reach 7.458 and the minimum 6.748cm of reaching 2.
Optimize nozzle passage width W 38 to guarantee to be derived from suitable the flowing and energy extraction of second level turbine nozzle 38.Increase or reduce nozzle passage width W 38 too little or too large by causing by flowing of first order turbine nozzle 38.Similarly, optimize flow region A38 and transmitted the working fluid of suitable quantity to guarantee second level turbine nozzle 38.Larger flow region A38 will cause the working fluid by first order turbine nozzle 38 too many, and less flow region A38 will cause working fluid very little.
Fig. 8 is the sectional view of ACM100.ACM100 is three-wheel ACM, contains fan part 102, compressor section 104 and turbine part 106, and it is all connected to axle 108.Axle 108 rotates about medial axis 110.
Fan part 102 comprises fan entrance 112 and fan outlet 114.Fan entrance 112 is from another source, as the opening in the ACM100 of the escape cock (not shown) reception working fluid in gas turbine engine.Fan outlet 114 allows working fluid to flee from fan part 102.Fan blade 116 can be used for working fluid suction fan part 102.
Compressor section 104 comprises suction port of compressor 118, compressor outlet 120 and compressor nozzle 122.This aperture reception sources, for limiting the pipeline in aperture, is wherein passed through from another source, as the working fluid to be compressed of fan part 102 in suction port of compressor 118.Once working fluid is compressed, 120 of compressor outlets allow working fluid to be directed to other system.Contracting machine nozzle 122 is the nozzle segment of the working fluid rotation by compressor section 104.Especially, compressor nozzle 122 is for radially going out circulation.
Turbine part 106 comprises turbine inlet 124, turbine outlet 126 and turbine nozzle 128.Turbine inlet 124 is for limiting the pipeline in aperture, and before wherein expanding in the first turbine part 106, working fluid is by this aperture.Turbine outlet 126 is for limiting the pipeline in aperture, and the working fluid wherein having expanded leaves turbine part 106 by this aperture.Turbine nozzle 128 is for extract the nozzle segment of energy from the working fluid by it, thereby driving turbine part 106 and appended assembly comprise the rotation of axle 108, fan part 102 and compressor section 104.
Axle 108 is bar, and as titanium pull bar, it is for connecting other assemblies of ACM100.The axis that medial axis 110 can arrange about it for other assemblies.
Fan part 102 is connected to compressor section 104.Especially, fan outlet 114 is attached to suction port of compressor 118, thereby working fluid can be transferred to suction port of compressor 118 from fan outlet 114.Suck working fluid and discharge working fluid by fan outlet 114 by fan entrance 112 through fan blade 116.Be directed to suction port of compressor 118 to compress from fan outlet 114 working fluid out compressor section 104.
Similarly, compressor section 104 and the first turbine part 106 are connected.Be directed to turbine inlet 124 from compressor outlet 120 working fluid out.Like this, working fluid passes through ACM100: first pass through fan entrance 112, follow by fan outlet 114, suction port of compressor 118, compressor outlet 120, turbine inlet 124 and turbine outlet 126.Between those ranks shown in Fig. 8, can there is extra rank.For example, heat exchanger (not shown) is often between compressor section 104 and turbine part 106.
Also warp beam 108 and connected with each other of each in fan part 102, compressor section 104 and turbine part 106.Axle 108 extends along medial axis 110 and is at least connected to compressor nozzle 122 and turbine nozzle 128.Fan blade 116 also can be connected to axle 20.
In the time that working fluid passes through ACM100, first in compressor section 104, compress, in turbine part 106, expand subsequently.Conventionally, in heat exchanger (not shown), also working fluid is heated or cooling, when working fluid between compressor section 104 and the first turbine part 106 by time, it determines route by heat exchanger.Turbine part 106 is extracted energy from working fluid, thereby about medial axis 110 rotatingshafts 20.
The adjustable working fluid by ACM100 is for being provided by gas turbine engine in the central chamber of vehicle of power.By compression, heating and expansion working fluid, can be adjusted to required temperature, pressure and/or relative humidity.But because compressor nozzle 122 and turbine nozzle 128 carry out fast rotational with respect to working fluid runner, therefore these parts need often to change.
Fig. 9 is the planimetric map of the turbine nozzle 128 that arranges about medial axis 110.Turbine nozzle 128 comprises 19 whole laminas 130 that arrange along disk 132 surfaces.Whole lamina 130 and disk 132 are by durable material, as made in steel, aluminium or titanium.Turbine nozzle 128 scribbles Tungsten carbite.Use HVOF be applied to the tungsten carbide coating on first order turbine nozzle 128, its allow improve hardness and with respect to other materials, as the Tungsten carbite of the higher percent of cobalt.With traditional painting method, as deposition-gun, spraying is compared, and HVOF spraying has also caused the variable reduction of coating thickness, as the more detailed description of carrying out with reference to Figure 15 A-15B.
Disk 132 is about medial axis 110 radial symmetric.Whole lamina 130 is equidistantly spaced apart each other along the girth of disk 132.Each in whole lamina 130 is all radially equidistantly away from medial axis 110.
The high value assembly of turbine nozzle 128 for changing more continually.Owing to contacting with abrasive particle, can cause the damage to turbine nozzle 128.Therefore, the coating of high-strength durable can improve the life-span of turbine nozzle 128.
Figure 10 is the side view of turbine nozzle 128.Turbine nozzle 128 contains whole lamina 130 and disk 132, as described in reference to Fig. 9.
Figure 10 shows the thickness of turbine nozzle 128.Especially, turbine nozzle 128 comprises blade height H128.Blade height H128 is disk 132 and adjacent component, as the head room amount between cover (not shown).In the first embodiment, blade height H128 is as shown in figure 10 0.318cm (0.125 inch).In second embodiment of quantity that need to increase working fluid stream, blade height H as shown in figure 10 can be 0.393cm (0.155 inch).In some versions of above-mentioned the first and second embodiments, the variation of blade height H128 can be up to 0.01cm (0.005 inch).But in order to make the working fluid of requirement by turbine part 106 (Fig. 8), the blade height H134 of 0.318cm or 0.393cm is desirable for ACM100 (Fig. 8).
Figure 11 is the enlarged view of a part for turbine nozzle 128.Shown the whole lamina 130 of being located on disk 132 at the enlarged portion shown in Figure 11.
Figure 11 shows the various concrete size of turbine nozzle 128.Nozzle passage width W 128 is the distance between each whole lamina 130 and the whole lamina 130 of radially adjoining.In fact throat's width that, nozzle passage width W 128 can be passed through for control air.Nozzle passage width W 128 is 0.241cm (0.095 inch), but its deviation can be up to 0.013cm (0.005 inch).Flow region A128 is the region that working fluid can be flowed through.Flow region A128 is the total surface area on the disk 132 in blade-side that is being equipped with that working fluid can flowed through between whole lamina 130.The part of the flow region A128 identifying in Figure 11 is the flow region A between a whole lamina 130 and the whole lamina 130 that is adjacent.In a word, the flow region A128 on the whole surface of turbine nozzle 128 is 1.451cm in the first above-mentioned embodiment 2(0.225 square inch), and be 1.806cm in the second above-mentioned embodiment 2(0.255 square inch).Minute differences due to processing and/or in applying, the variation of these values can be up to 5%.
Optimize nozzle passage width W 128 to guarantee to be derived from suitable the flowing and energy extraction of turbine nozzle 128.Increase or reduce nozzle passage width W 128 by the fluid of the nozzle 128A that causes flowing through too much or very little.Similarly, optimize flow region A128 and transmitted the working fluid of suitable quantity to guarantee first order turbine nozzle 128.Larger flow region A128 will cause the working fluid by turbine nozzle 128 too many, and less flow region A128 will cause working fluid very little.
Figure 12 is the planimetric map of turbine nozzle 128A, and this turbine nozzle 128A is the alternate embodiment that can be used in three-wheel ACM100.Also can turbine nozzle 128A be set about medial axis 110.The same with the turbine nozzle 128 of describing above with reference to Fig. 8-11, turbine nozzle 128A also can be used in ACM100 (Fig. 8).Turbine nozzle 128A comprises 23 whole lamina 130A that arrange along the surface of disk 132A.Whole lamina 130A and disk 132A are by durable material, as made in steel, aluminium or titanium.Turbine nozzle 128A scribbles Tungsten carbite.Use HVOF spraying to be applied to the tungsten carbide coating on turbine nozzle 128A, it allows the hardness that improves and with respect to other materials, as the Tungsten carbite of the higher percent of cobalt.
Disk 132A is about medial axis 110 radial symmetric.Whole lamina 130A is equidistantly spaced apart each other along the girth of disk 132A.Therefore, whole lamina 130A is between two adjacent whole lamina 130A, and each in whole lamina 130A is radially equidistantly away from medial axis 110.
Turbine nozzle 128A is the high value assembly that will change more continually.Owing to thering is abrasive particle in the high velocity air of turbine nozzle 128A guiding, may cause the damage to turbine nozzle 128A.Therefore the coating that, the height on second level turbine nozzle 128A is durable can improve its life-span.
Figure 13 is the side view of turbine nozzle 128A.Turbine nozzle 128A contains whole lamina 130A and disk 132A, as described in reference to Figure 12.
Figure 13 shows the thickness of turbine nozzle 128A.Especially, turbine nozzle 128A comprises blade height H128A.Blade height H128A is disk 132A and adjacent component, as the head room amount between cover (not shown).Blade height H128A shown in Figure 13 is 0.305cm (0.120 inch).In certain embodiments, the variation of blade height H128A can be up to 0.01cm (0.005 inch).But in order to make the working fluid of aequum by turbine part 106 (Fig. 8), the blade height H128A of 0.305cm is desirable.
Figure 14 is the enlarged view of a part of turbine nozzle 128A.Shown the whole lamina 130A being located on disk 132A at the enlarged portion shown in Figure 14.
Figure 14 shows the various concrete size of turbine nozzle 128A.Nozzle passage width W 128A is the distance between the whole lamina 130A that each whole lamina 130A is adjacent with it.In fact, nozzle passage width W 128A is throat's width that working fluid can pass through.Nozzle passage width W 128A is 0.234cm (0.092 inch), but its deviation can be up to 0.013cm (0.005 inch).Flow region A128A is the be equipped with cross-section area that blade-side can flow through of fluid at the disk 132A between whole lamina 130A.The part of the flow region A128A identifying in Figure 14 is the flow region A between a whole lamina 130A and the whole lamina 130A that is adjacent.In a word, in turbine nozzle 128A, the whole flow region A128A filling on vaned surface side of disk 132A is 1.639cm 2(0.254 square inch).Minute differences due to processing and/or in applying, this value can reach 1.721cm 2and the minimum 1.557cm that reaches 2.
Optimize nozzle passage width W 128A to guarantee to be derived from suitable the flowing and energy extraction of turbine nozzle 128A.Increasing or reduce nozzle passage width W 128A will cause the fluid stream by turbine nozzle 128A too large or too little.Similarly, optimize flow region A128A and transmitted the working fluid of suitable quantity to guarantee turbine nozzle 128A.Larger flow region A128A will cause the working fluid by turbine nozzle 128A too many, and less flow region A128A will cause working fluid very little.
Each aforesaid turbine nozzle embodiment all has coating.Use HVOF to apply coating.Therefore, each aforesaid turbine nozzle all has by accepting substrate material scope, as the made substrate of any material in steel, aluminium, pottery or titanium.Use HVOF by coating spraying to substrate, and this coating is mainly made up of Tungsten carbite.Before, use pinking rifle to apply and apply coating.
The coating applying is not pure WC.For the ease of using pinking rifle technology to apply, coating is often made up of 12% ± 2% cobalt.Correspondingly, cover coat has the bonding strength of 8500psi ± 5%.But, using HVOF, coating can have the Tungsten carbite of higher percentage.The coating that uses HVOF to apply is often made up of 9% ± 2% cobalt.Conventionally, coating can contain the cobalt that is less than 8 volume %.Correspondingly, cover coat 164 has the bonding strength of 10,000psi ± 5%.
The coating that uses pinking rifle technology to apply has the minimum thickness that is approximately 0.00254cm (0.001 inch) conventionally.These coatings of the prior art have the scope that is approximately 0.00762cm (0.003 inch) ± 2% conventionally.The common scope will with the minimum thickness and the 0.00508cm (0.002 inch) that are approximately 0.00508cm (0.002 inch) of coating that uses HVOF to apply.
Potential embodiment's example
Below the possible embodiment of nonexcludability of the present invention.
For a nozzle for air cycle machine, comprise the integrated disc portions with medial axis.Multiple blades, it is from vaned extended blade height H of filling of described integrated disc portions, and described multiple blades are radially arranged about described integrated disc portions.Each radially adjoinings of described multiple turbine blades between throat's width W of limiting.The coating of the described integrated disc portions of basic encapsulation and described multiple blades, wherein said coating contains the Tungsten carbite that is greater than 91 volume %.
Nozzle in leading portion comprises any one or more in extra and/or other following feature, configuration and/or other parts alternatively.
Described nozzle can have multiple blades, and wherein said multiple blades can be made up of 34 blades.
The described blade height H of described nozzle can be 0.940cm, and throat's width is 0.222cm.
Described nozzle also can comprise the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A can equal 7.103cm 2.
Described nozzle can have multiple blades, and wherein said multiple blades are made up of 19 blades.
The described blade height H of described nozzle can be 0.686cm, and throat's width is 0.340cm.
Described nozzle also can comprise the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A can equal 4.432cm 2.
Described blade height H can be 0.318cm, and throat's width can be 0.241cm.
Described blade height H can be 0.393cm, and throat's width can be 0.241cm.
The described surface area that fills vaned flow region A that limit and between described blade along described disk can equal 1.451cm 2.Another scheme is that described flow region A can equal 1.806cm 2.
Described multiple blade can be made up of 23 blades.
Described blade height H can be 0.305cm, and throat's width can be 0.234cm.
Described nozzle also can comprise the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A can equal 1.639cm 2.
Described coating can comprise metal alloy, and it has the cover coat bonding strength that is greater than 10,000psi.
Described coating comprises metal alloy, and it has the cover coat bonding strength that is greater than 10,000psi.
According to another embodiment of the present invention, a kind of nozzle for air cycle machine, comprises disk and multiple blade.Integrated disc portions has medial axis.Multiple blades, it is from vaned extended blade height H of filling of described integrated disc portions.Described multiple blade is radially arranged about described integrated disc portions.Each radially adjoinings of described multiple turbine blades between throat's width W of limiting.The coating of the described integrated disc portions of basic encapsulation and described multiple blades, wherein said coating has the thickness of 50.8 μ m-101.6 μ m.
Nozzle in leading portion comprises any one or more in extra and/or other following feature, configuration and/or other parts alternatively.
Described coating can contain the cobalt that is less than 8 volume %.
Described multiple blade can be made up of 34 blades.
Described blade height H can be 0.940cm.
Described throat width can be 0.222cm.
Described nozzle also can comprise the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A can equal 7.103cm 2.
Described multiple blade can be made up of 19 blades.
Described blade height H can be 0.686cm.
Described throat width can be 0.340cm.
Described flow region A can equal 4.432cm 2.
Described blade height H can be 0.318cm.
Described blade height H can be 0.393cm.
Described throat width can be 0.241cm.
Described flow region A can equal 1.451cm 2.
Described flow region A can equal 1.806cm 2.
Described multiple blade can be made up of 23 blades.
Described blade height H can be 0.305cm.
Described throat width can be 0.234cm.
Described flow region A can equal 1.639cm 2.
Described coating can comprise metal alloy, and it has the surperficial bonding strength that is greater than 10,000psi.
According to still another embodiment of the invention, a kind of nozzle for air cycle machine, comprising: integrated disc portions and multiple blade.Integrated disc portions comprises medial axis.Multiple blades, it is from vaned extended blade height H of filling of described integrated disc portions, and described multiple blades are radially arranged about described integrated disc portions.Each radially adjoinings of described multiple turbine blades between throat's width W of limiting.The coating of the described integrated disc portions of basic encapsulation and described multiple blades, wherein said coating comprises metal alloy, it has the cover coat bonding strength that is greater than 10,000psi.
Nozzle in leading portion comprises any one or more in extra and/or other following feature, configuration and/or other parts alternatively.
Described coating can contain the cobalt that is less than 8 volume %.
Described multiple blade can be made up of 34 blades.
Described blade height H can be 0.940cm.
Described throat width can be 0.222cm.
Described nozzle also can comprise the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A can equal 7.103cm 2.
Described multiple blade can be made up of 19 blades.
Described blade height H can be 0.686cm.
Described throat width can be 0.340cm.
Described flow region A can equal 4.432cm 2.
Described blade height H can be 0.318cm.
Described blade height H can be 0.393cm.
The described width H of throat can be 0.241cm.
Described flow region A can equal 1.451cm 2.
Described flow region A can equal 1.806cm 2.
Described multiple blade can be made up of 23 blades.
Described blade height H can be 0.305cm.
Described throat width can be 0.234cm.
Described flow region A can equal 1.639cm 2.
Although described the present invention with reference to exemplary embodiment, it will be apparent to one skilled in the art that and replace element wherein can carry out without departing from the scope of the invention various variations available equivalents.In addition,, in the situation that not departing from base region of the present invention, many amendments can be carried out so that particular case or material adapt to religious doctrine of the present invention.Therefore, the present invention is not limited to invented specific embodiment, and the present invention will comprise all embodiments that drop within the scope of appended claims.

Claims (15)

1. for a nozzle for air cycle machine, comprising:
There is the integrated disc portions of medial axis;
Multiple blades, it is from vaned extended blade height H of filling of described integrated disc portions, and described multiple blades are radially arranged about described integrated disc portions;
Each radially adjoinings of described multiple turbine blades between throat's width W of limiting; And
The coating of the described integrated disc portions of basic encapsulation and described multiple blades, wherein said coating contains the Tungsten carbite that is greater than 91 volume %.
2. nozzle according to claim 1, wherein said multiple blades are made up of 34 blades.
3. nozzle according to claim 1 and 2, wherein said blade height H is 0.940cm; And described throat width is 0.222cm.
4. according to the nozzle described in claim 1 or 2 or 3, and also comprise the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A equals 7.103cm 2.
5. nozzle according to claim 1, wherein said multiple blades are made up of 19 blades.
6. nozzle according to claim 1 or 5, wherein said blade height H is 0.686cm; And described throat width is 0.340cm.
7. according to the nozzle described in claim 1 or 5 or 6, and also comprise the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A equals 4.432cm 2.
8. nozzle according to claim 1, wherein said blade height H is 0.318cm; And described throat width is 0.241cm.
9. nozzle according to claim 1, wherein said blade height H is 0.393cm; And described throat width is 0.241cm.
10. according to the nozzle described in claim 1 or 8 or 9, and also comprise the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A equals 1.451cm 2.
11. according to the nozzle described in claim 1 or 8 or 9, and also comprises the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A equals 1.806cm 2.
12. nozzles according to claim 1, wherein said multiple blades are made up of 23 blades.
13. nozzles according to claim 1, wherein said blade height H is 0.305cm; And described throat width is 0.234cm.
14. according to the nozzle described in claim 1 or 12 or 13, and also comprises the described surface area that fills vaned the flow region A that limit and between described blade along described disk, and wherein said flow region A equals 1.639cm 2.
15. according to the nozzle described in any one of aforementioned claim, and wherein said coating comprises metal alloy, and it has the surperficial bonding strength that is greater than 10,000psi.
CN201410125935.2A 2013-04-24 2014-03-31 Turbine nozzle piece parts with HVOC coatings Pending CN104121228A (en)

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