CN102536889B - Compressor blade, possess its turbine and the method suppressing its friction collision - Google Patents
Compressor blade, possess its turbine and the method suppressing its friction collision Download PDFInfo
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- CN102536889B CN102536889B CN201110404686.7A CN201110404686A CN102536889B CN 102536889 B CN102536889 B CN 102536889B CN 201110404686 A CN201110404686 A CN 201110404686A CN 102536889 B CN102536889 B CN 102536889B
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- blade
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- turbine
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
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Abstract
The present invention relates to compressor blade and the method for its friction collision of suppression.The compressor blade (22) of a kind of friction collision for suppression between the blade tip (26) of compressor section (20) intra vane (22) of turbine and the inner surface (42) of the housing (24) surrounding rotating hardware and method.This compressor blade (22) includes that cap (28), cap (28) are limited to the blade tip (26) at the radially end of blade (22) and the multiple flexible members (30) extended from cap (28) surface limiting blade tip (26).Flexible member (30) extends from surface in the spanwise of blade (22), and rigidity can be become by operation due to the centrifugal rigidifying under compressor operation speed, and in the inner surface (42) of housing (24), cut out groove (44) alternatively.
Description
Technical field
The present invention is related generally to turbine, the compressor of such as gas-turbine unit.More particularly, the present invention relates to compressor blade, its top combines flexible cutting elements, the risk on the damaged blade top occurred for reducing the frictional impact of housing being likely to be due to and surrounding compressor.
Background technology
Gas-turbine unit operates generally based on following principle: at the compressor section compressed air of electromotor, and then compressed air is delivered to the combustion sec-tion of electromotor, and in combustion sec-tion, fuel adds air to and lights.Afterwards, obtained ignition mixture being delivered to the turbine section of electromotor, wherein, combustion process a part for the energy generated is extracted to drive engine compressor by turbine.
Compressor includes that the rotating hardware in one or more dishes or rotor configurations, airfoil (blade) extend radially across the air flow path by this electromotor therefrom.The radially outer boundary of the air flow path in compressor section is limited by the housing surrounding rotating hardware.The air that this housing is come in for delivery is through the compressor to ensure that the large quantity of air entering this electromotor will be by compressor compresses.But, fraction air can by the outer airflow path in compressor section, between blade tip and housing exist radial clearance and get around compressor blade.Owing in compressor section, the air of compression, for supplying the turbine section of electromotor, can get around the amount of air of compressor blade by this gap by restriction and improve engine efficiency.Therefore, rotating hardware and the housing of compressor section are manufactured into close tolerance, in order to minimize this gap.
Manufacturing tolerance, different coefficient of thermal expansions and kinetic effect limit the degree that can reduce this gap.As an example, the internal diameter of housing is circular and concentric with the rotation axis of compressor the most veritably.Accordingly, there exist and break through airfoil to the space of housing and the situation of blade tip friction housing.Blade tip friction damage can be different in terms of form with seriousness.Can be the form of one or more cracking or burr to the damage of blade tip, it can pass through local vibration mode propagation in tip region.For example, Fig. 4 schematically shows serious top burr (stress concentration portion) 14 caused due to the plastic deformation at the top 12 of blade 10.If top burr 14 are enough serious, the stress formed is concentrated can amplify the vibration stress caused by the modal vibration of top, and causes high cycle fatigue (HCF) life deterioration of blade 10.Also local friction can be occurred due to blade rubbing to heat, and local friction's heating may result in and forms fragility heat affected area (HAZ) 16 at blade tip 12.
Propose several scheme to solve blade tip damage and the problem of the leakage of the air at outer airflow path.A kind of scheme relates to the internal diameter application abradable material to compressor housing so that sacrificial is worn away by abradable material when being rubbed by blade tip.Another program is to combine cut edge (" groove-like (squealer) top ") at blade tip.In all cases, during initial engine operates, blade tip cuts out groove in housing inner diameter, produces more tortuous path at outer airflow path, between housing and blade tip.Although effective, but two kinds of technology implementations are got up the most costly.As an example, the cut edge of blade tip is typically formed by coating, and coating is likely difficult to deposit to adequate thickness, with the serious lower survival of friction collision common in hardware at the scene.On the other hand, the deposition of the abradable coating on compressor housing internal diameter needs close quality control to produce suitably composition, and including particle/void ratio and distribution, it can avoid the suitable hardness of blade tip damage during wear events by presenting.Friction with the hardest abradable coating is collided and will be caused scraping or cracking at blade tip, and the continuation operation of electromotor can make to swipe and serve as the initiation site of the cracking subsequently caused due to vibration stress.On the contrary, too soft abradable coating can eat away owing to the high-speed gas in compressor section flows.
In light of the above, it is desirable to the technology of the improvement for reducing the air leakage at the outer airflow path of blade tip damage and compressor.
Summary of the invention
The invention provides the compressor blade of the component of the rotating hardware in a kind of compressor section being suitable for use as turbine and for the method for suppression friction collision between the blade tip of blade and the inner surface of the housing that surrounds this rotating hardware.
According to the first aspect of the invention, this compressor blade includes that cap, cap are limited to the blade tip at the radially end of blade and multiple flexible members of the surface extension from the cap limiting blade tip.Flexible member extends from surface in the spanwise of blade, and can become rigidity by operation due to the centrifugal rigidifying under compressor operation speed.Flexible member is optionally able to be cut out in the inner surface of housing under compressor operation speed groove by operation, or can be formed by smooth non-cutting material.
Another aspect of the invention is a kind of method, it includes being formed in compressor blade it and radially has the first joint interface at end；Cap is made there is such second joint interface: this second joint interface has the shape complementary with the first joint interface of blade；And multiple flexible members of the cap surface extension being oppositely disposed from the second joint interface with cap are provided.Then cap is joined to blade so that the first joint interface and the second joint interface form metallurgical joint；The surface of cap limits the blade tip of blade, and flexible member extends from blade in the spanwise of blade.Flexible member is optionally able to cut out groove by operation in the inner surface surround the housing of other rotating hardware of blade and compressor section, or can be formed by smooth non-cutting material.
The method have technical effect that the following ability of flexible member: eliminate or alleviate blade tip the most sharp owing to colliding and impaired risk with rubbing of the compressor housing of the remainder surrounding blade and compressor rotating hardware.For example, flexible member may be adapted to cut out groove in the inner surface of housing.Due to the result cut by flexible member, groove is substantially coaxial with the rotation axis of rotating hardware, and the most spaced apart with the blade tip of blade.Groove is further able to be sealed the air leakage reducing the outer airflow path by compressor by the outer flow path improving between blade tip and shell inner surface.Alternatively, flexible member can be limited to the inner surface with housing and forms sealing.
By detailed description below, other aspects and advantages of the present invention will be best understood from.
Accompanying drawing explanation
Fig. 1 represents the front view of compressor blade and the adjacent part of the compressor housing surrounding compressor rotating hardware with the blade tip according to embodiments of the invention structure, and blade is the component of compressor rotating hardware.
Fig. 2 is the detail drawing of the adjacent part of the blade tip cap of Fig. 1 and blade before cap is attached on blade the blade tip to form Fig. 1.
Fig. 3 is the detailed perspective view of the blade tip cap of Fig. 2, and represents for the technology of retaining component in cap.
Fig. 4 represents the tip region of prior art compressor blade, and depict can the damage to the several type that blade tip occurs due to the friction collision with compressor housing.
List of parts:
10 blades
12 tops
14 top burr
16th district
20 sections
22 blades
24 housings
26 tops
28 caps
30 elements
31 materials
32 joints
34 ends
36 junctions
38 junctions
40 disturbance parts
42 surfaces
44 grooves
Detailed description of the invention
Fig. 1 schematically shows a part for the compressor section 20 of turbine (such as, industry or aircraft gas turbine engines).The single compressor blade 22 of compressor section 20 is shown, it will be appreciated that blade 22 is in multiple blade 22.Blade and their attached dishes (not shown) form a part for the rotating hardware in compressor section 20.Also illustrate that in FIG the rotating hardware of compressor section 20 by housing 24 around, a part for housing 24 is expressed as radially top 26 against blade 22.The air that housing 24 is flowed by compressor for delivery is to guarantee that the large quantity of air entering electromotor 10 will compress in compressor section 20.Little radial clearance is present between blade tip 26 and housing 24.Minimize this gap and can promote that compressor section 20 and electromotor are as overall efficiency.
According to a preferred aspect of the present invention, blade 22 is provided with the component by being referred to as blade tip cap 28, and it forms the outer radial end (top 26) of blade 22.Cap 28 combines cutting element 30, and cutting element 30 expection prevents or at least minimize the friction between blade tip 26 and compressor housing 24, and this friction may result in the HCF life deterioration of blade 22.Cutting element 30 can also be used for promoting that the outer flow path with housing 24 seals by forming more tortuous flow path between blade tip 26 and housing 24.
In fig. 1 and 2, cutting element 30 is expressed as multiple silks or the fiber being spaced apart from each other in the chordwise direction of blade tip 26 and extending from blade tip 26 on the direction of spanwise axis being arranged essentially parallel to blade 22.Element 30 is suitable to the inner surface 42 that the housing 24 of blade 22 is surrounded in cutting, but the most lightweight, in order to blade 22 is contributed the parasitic of minimum.As represented by fig. 2 with dotted line, element 30 is preferably flexible, but then becomes rigidity due to the physical phenomenon of " centrifugal rigidifying " under compressor operation speed.Element 30 can serve as the cutting element of the inner surface 42 against housing 24 when rigidifying under compressor operation speed, and cuts out specific inner surface 42 during do so in shell inner surface 42 closer to the groove 44 coaxial with the rotation axis of the rotating hardware of compressor.It practice, element 30 is concentric with the rotation axis of compressor rotating hardware for the inner surface 42 making the most non-round housing 24.As from Fig. 1 it is obvious that groove 44 is the most spaced apart with the blade tip 26 of blade 22, correspond roughly to the length of element 30, thus eliminate or alleviate the most sharp the risk of the blade tip damage caused due to the friction collision with housing 24.Although Fig. 1 and Fig. 2 depicts five elements 30 of existence, but can use less amount or more substantial element 30.Generally, it is believed that at least one hundred element 30 (every square centimeter of at least about 15 elements 30) should be present at blade tip 26 per square inch, in order to realize sufficient cutting efficiency.Preferably limit the quantity of element 30 so that adjacent elements 30 is attached at the respective point of cap 28 be spaced apart from each other at it so that element 30 keeps its bending ability.As an example, it may be necessary to the quantity limiting element 30 is the most about 600 elements 30 (every square centimeter of about 100 elements 30).
Element 30 can be formed by multiple material, and (such as, its notable example includes stainless steel silk, carbon steel wire, carbon fiber, aromatic polyamides) fiber, alumina fibre and silicon carbide fibre.In order to strengthen its cutting power, element 30 can be applied the abrasion coating formed by such as cubic boron nitride, aluminium oxide, diamond, tungsten carbide or other hard grind consumption material.At present, it is believed that alumina fibre and carbon fiber with cubic boron nitride coating are preferred.Suitable procedure for generating element 30 includes that such as carbon steel and stainless steel wire drawing and rotation sol gel or other precursor are to produce the conventional method of ceramic fibre.Abrasion coating or particle can be coated by various technology, such as coating, soldering or resin-bonded.Appropriate length and the diameter of element 30 will depend partially on application-specific.But, the length of element 30 and diameter affect flexibility and the cutting power of element 30, and it is taken as that there is some and limit.For example, it is believed that element 30 should have the length of at least 2.5 millimeters and be about 8.5 millimeters, preferably scope is of about 4 millimeters to about 6 millimeters.Furthermore, it is believed that element 30 should have the diameter of at least 17 microns and can arrive greatly about 500 microns, preferably scope is of about 125 microns to about 300 microns.
Fig. 2 illustrates the blade tip 26 being embedded in cap 28 and formed by cap 28 and the inner of the element 30 of projection.Fig. 3 represents cap 28 to be formed in the surface limiting blade tip 26 and comprises surface cavity or groove, and illustrates the result utilizing material 31 filling slot anchored to by element 30 on cap 28.For example, groove can be filled resin, brazing alloy or can fix under the operating condition of blade 10 and other material of retaining component 30.The conventional methods such as such as electro-discharge machining (EDM), grinding, milling are included for producing the suitable procedure of cap 28.Cap 28 is preferably formed by with the alloy for forming the alloy of blade 22 compatible.In the compressor blade for industrial gas turbine engine is applied, the notable example of blade alloy includes the ferrous alloy containing chromium, such as GTD-450, AISI 403 and AISI 403+Cb.Chemical compatibility use such as soldering and welding (include use just be soldered parts between friction to generate the solder technology of welding temperature) process by the ability in cap 28 metallurgical, bond to blade 22 in terms of particular importance.In view of these consider, the alloy being considered particularly suitable for use in the blade that cap 28 and being subsequently joined to is formed by ferrous alloy includes GTD-450 and AISI 403+Cb.As mentioned above, including soldering, welding and friction welding for engaging the suitable procedure of cap 28 and blade tip 34, wherein soldering is considered method for optimizing at present.
Cap 28 is expressed as making the end 34 with the blade 22 attached by this cap 28 the most in fig. 1 and 2 and forms double scarved joint 32.Joint interface 36 and 38 is limited on this pair of scarved joint 32 each in blade tip 34 and cap 28 respectively.Joint interface 36 and 38 has shape complimentary to one another, and each joint interface 36 and 38 includes a pair faying surface, and faying surface is tilted and be both not parallel to the spanwise axis of blade 22 to be also not orthogonal to the spanwise axis of blade 22 by toward each other.Fig. 2 also illustrates that the joint interface 36 of blade tip 34 combines disturbance part (perturbation) 40 and promotes the metallurgy at joint 32 and mechanical interlocking, thus provides structural load paths redundancy to resist the typical case being present in blade 22 under compressor operation speed high centrifugal stress field.Alternately or as supplement, the joint interface 38 of cap 28 is formed as including being similar to disturbance part 40 or the disturbance part with disturbance part 40 complementation.Joint construction known to other is also possible, including one of joint interface 36 and 38 being formed as dovetail and another being formed as the dovetail groove of complementation.
Owing to element 30 cuts out groove 44 in the inner surface 42 of housing 24, will due to housing 24 rub collision and the probability on damaged blade top 26 can significantly reduce (without eliminate if).Therefore, can avoid or alleviate typical damage type, including the small and serious top burr 14 represented by fragility HAZ 16 and Fig. 4, it may cause cracking, and by propagation subsequently, the HCF life deterioration of blade 22 can be made and cause the tip fracture driven by airfoil modal.Think that the flexibility of element 30 is particularly advantageous, because its flexibility makes element 30 can be less prone to when the collision that occurs seriously to rub (in the turbine of such as gas-turbine unit common) and is completely removed.Additionally, contrary with most of elements 30, Individual elements 30 more likely can be lost so that cap 28 can continue to provide a certain degree of dissection to housing 24, and owing to friction subsequently is collided, this dissection is probably necessity.
In some cases it is contemplated that the ability cutting out groove 44 in the inner surface 42 of housing 24 of element 30 may be not necessarily.Therefore, flexible member 30 is formed as smooth and non-cutting, and the most only flexure when contacting housing 24 by the alternative aspect of the present invention.Think that smooth non-cutting element 30 can reduce the risk damaging top 26, and the radial gap gap being sealed between blade tip 26 and compressor housing 24.In most cases, the suitable lubricious material for non-cutting element 30 will be limited to the relatively early level of industrial gas turbine compressor.These materials substantially but limiting examples includes such as carbon fiber or polymer fiber-such asFiber-fibrous material.
Although describing the present invention about preferred embodiment, it is apparent that those skilled in the art may be used without other form.For example, blade tip cap 28 can be different from illustrated configuration with the physique of element 30.It is also foreseeable that the present invention can be applied in combination with the abradable material being attached to directly about in housing 24 region on compressor blade top.Therefore, the scope of the present invention is only limited by the following claims.
Claims (8)
1. a compressor blade (22), be configured to suppress this blade blade tip (26) with
Friction collision between the inner surface (42) of the housing (24) surrounding compressor rotating hardware, this compression
Machine rotating hardware includes that described blade (22), described blade (22) including:
Cap (28), is limited to the described blade tip at the radially end of described blade (22)
(26)；
Multiple flexible members (30), from the surface of the described cap (28) limiting described blade tip (26)
Extending, described flexible member (30) prolongs from described surface in the spanwise of described blade (22)
Stretching, described flexible member (30) can be by operation due to being centrifuged just at compressor operation speed
Change and become rigidity,
Described flexible member (30) includes flexible cutting elements (30), described flexible cutting elements (30)
Can be by operating in the described inner surface (42) of described housing (24) under compressor operation speed
Cut out substantially coaxial with the rotation axis of described compressor rotating hardware groove (44).
Compressor blade the most according to claim 1 (22), it is characterised in that described soft
Property element (30) is present on the surface of described cap (28) with the amount of every square centimeter at least ten five.
Compressor blade the most according to claim 1 and 2 (22), it is characterised in that institute
State flexible member (30) by selected from stainless steel silk, carbon steel wire, carbon fiber, aramid fibre,
The material of the group of alumina fibre and silicon carbide fibre composition is formed.
Compressor blade the most according to claim 3 (22), it is characterised in that described soft
Property element (30) include wear material coating, described wear material coating promotes described flexible member
(30) relative to the abrasivity of described inner surface (42) of described housing (24).
Compressor blade the most according to claim 1 and 2 (22), it is characterised in that institute
State flexible member (30) by the smooth non-cutting material of the group formed selected from carbon fiber and polymer fiber
Formed.
Compressor blade the most according to claim 1 (22), it is characterised in that described leaf
Sheet (22) is installed on the pressure of described turbine as the part of the compressor rotating hardware of turbine
In compressor portion section (20), the inner surface (42) of described housing (24) surrounds described compressor and rotates hard
Part, and described flexible member (30) cuts out groove in the inner surface (42) of described housing (24)
(44)。
7. a turbine, it is characterised in that it includes the compressor leaf described in claim 6
Sheet (22), and described turbine is gas-turbine unit.
8. the blade tip (26) suppressed in compressor blade (22) rotates with surrounding compressor
The method of the friction collision between the inner surface (42) of the housing (24) of hardware, described compressor rotates
Hardware includes described blade (22), and described method includes:
Described blade (22) is formed at the radially end of this blade there is the first joint handing-over
Portion (36)；
Cap (28) is made there is the second joint interface (38), described second joint interface (38)
There is the shape that described first joint interface (36) with described blade (22) is complementary；
The described cap being oppositely disposed from the second joint interface (38) with described cap (28) is provided
(28) multiple flexible members (30) that surface extends；
Described cap (28) is joined to described blade (22) so that described first joint interface and
Two joint interface (36,38) form metallurgical joint (32), and the described surface of described cap (28) limits
The blade tip (26) of described blade (22), and described flexible member (30) is at described blade (22)
Extend from described blade (22) in spanwise,
Described method also includes:
Described blade (22) is installed on institute as the part of the compressor rotating hardware of turbine
State in the compressor section (20) of turbine；And
Operate described turbine so that described flexible member (30) becomes firm due to centrifugal rigidifying
Property, and cutting in surrounding the described inner surface (42) of described housing (24) of compressor rotating hardware
Go out substantially coaxial with the rotation axis of described compressor rotating hardware groove (44).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/955,009 US8845283B2 (en) | 2010-11-29 | 2010-11-29 | Compressor blade with flexible tip elements and process therefor |
| US12/955009 | 2010-11-29 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102536889A CN102536889A (en) | 2012-07-04 |
| CN102536889B true CN102536889B (en) | 2016-12-14 |
Family
ID=
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|---|---|---|---|---|
| US5752802A (en) * | 1996-12-19 | 1998-05-19 | Solar Turbines Incorporated | Sealing apparatus for airfoils of gas turbine engines |
| EP0947746A2 (en) * | 1998-04-03 | 1999-10-06 | General Electric Company | Bucket cover geometry for brush seal applications |
| US6171351B1 (en) * | 1994-09-16 | 2001-01-09 | MTU Motoren-und Turbinen Union M{umlaut over (u)}nchen GmbH | Strip coatings for metal components of drive units and their process of manufacture |
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| US7549841B1 (en) * | 2005-09-03 | 2009-06-23 | Florida Turbine Technologies, Inc. | Pressure balanced centrifugal tip seal |
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6171351B1 (en) * | 1994-09-16 | 2001-01-09 | MTU Motoren-und Turbinen Union M{umlaut over (u)}nchen GmbH | Strip coatings for metal components of drive units and their process of manufacture |
| US5752802A (en) * | 1996-12-19 | 1998-05-19 | Solar Turbines Incorporated | Sealing apparatus for airfoils of gas turbine engines |
| EP0947746A2 (en) * | 1998-04-03 | 1999-10-06 | General Electric Company | Bucket cover geometry for brush seal applications |
| US7549841B1 (en) * | 2005-09-03 | 2009-06-23 | Florida Turbine Technologies, Inc. | Pressure balanced centrifugal tip seal |
| CN201106578Y (en) * | 2007-09-28 | 2008-08-27 | 大连海事大学 | Intermediate axle rotating extrusion compression roter based on bow-wave compression technique |
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