CN102852566A - Turbine seal system - Google Patents
Turbine seal system Download PDFInfo
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- CN102852566A CN102852566A CN2012102017506A CN201210201750A CN102852566A CN 102852566 A CN102852566 A CN 102852566A CN 2012102017506 A CN2012102017506 A CN 2012102017506A CN 201210201750 A CN201210201750 A CN 201210201750A CN 102852566 A CN102852566 A CN 102852566A
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- Prior art keywords
- seal assembly
- stage
- turbine
- interstage seal
- impeller
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
A system includes a multi-stage turbine. The multi-stage turbine includes a first turbine stage including a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel, a second turbine stage including a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel, and an interstage seal extending axially between the first and second turbine stages. The interstage seal is configured to be installed or removed while the first and second wheels remain in place in the respective first and second turbine stages.
Description
Technical field
The present invention relates to the combustion gas turbine technical field, exactly, relate to the Sealing technology in the turbo machine.
Background technique
Generally, the mixture of gas turbine engine burning pressurized air and fuel is to produce hot combustion gas.Described combustion gas can flow through one or more turbine stages, thereby are load and/or compressor generating.Pressure drop can occur in inter-stage, thereby can make fluid, and combustion gas for example by path improperly leakage current occur.Can between described level, Sealing be set, to reduce the fluid leakage between the level.But unfortunately, Sealing can meet with stresses, thermal stress for example, thus can be at the described Sealing of upper offset axially and/or radially, and then reduce the effectiveness of described Sealing.For example, Sealing deflection can increase the possibility that friction occurs between fixed component and the rotary component.
Summary of the invention
This specification will be summarized some embodiment in the initial scope of the present invention.These embodiments' purpose and not lying in limits the scope of the invention, and only be to summarize of the present invention may form.In fact, the present invention may comprise from following embodiment's form class like or different various forms.
In the first embodiment, a kind of system provided by the present invention comprises multi-stage turbine.Described multi-stage turbine comprises: the first turbine stage, and it comprises the first impeller, described the first impeller has a plurality of the first blade sections that circumferentially are distributed in around described the first impeller; The second turbine stage, it comprises the second impeller, described the second impeller has a plurality of the second blade sections that circumferentially are distributed in around described the second impeller; And interstage seal assembly, it extends axially between described the first turbine stage and described the second turbine stage.Described interstage seal assembly is configured to carry out installation or removal when described the first impeller and described the second impeller remain in original position in corresponding described the first turbine stage and described the second turbine stage.
Each blade sections in described a plurality of the first blade sections uses a plurality of the first assembling sets to be connected to described the first impeller, and each blade sections in described a plurality of the second blade sections uses a plurality of the second assembling sets to be connected to described the second impeller.Each first assembling set comprises to be located at the first groove in described the first impeller and to be located at first key shape thing in the blade sections in described a plurality of the first blade sections, and each second assembling set comprises and is located at the second groove in described the second impeller and is located at the second key shape thing in the blade sections in described a plurality of the second blade sections.
Described interstage seal assembly is configured to can pivot towards the axial axis of described multi-stage turbine during described interstage seal assembly is installed, and described interstage seal assembly is configured to can pivot away from the described axial axis of described multi-stage turbine during the described interstage seal assembly of dismounting.Described interstage seal assembly comprises the inclination ribs that becomes certain angle with the interior bridge portion of described interstage seal assembly, wherein said inclination ribs make described interstage seal assembly can towards and pivot away from the axial axis of described multi-stage turbine.Described interstage seal assembly comprises second recess part adjacent with described inclination ribs, described the second recess part is configured to take in the second portion of described the second impeller, thereby make described interstage seal assembly can towards with pivot away from described axial axis, and the first recess part of described interstage seal assembly is configured at described interstage seal assembly along described axial axis is taken in described the first impeller when described the first turbine stage moves first portion.Described angle less than approximately 75 the degree.
Described interstage seal assembly comprises the first support feature, its be configured to be arranged at described a plurality of the first blade sections or described a plurality of the second blade sections in the second support feature on one or more blade sections cooperate, stoping described interstage seal assembly during the described interstage seal assembly of installation or removal, to move radially towards the axial axis of described multi-stage turbine, and stop described interstage seal assembly circumferentially mobile around described axial axis at described multi-stage turbine operation run duration.Described the first support feature comprises groove, and described the second support feature comprises key shape thing.Described interstage seal assembly comprises the axial end part, and it is configured to cooperate diametrically at described multi-stage turbine run duration the wheel rim of described the first impeller or described the second impeller.
Described interstage seal assembly also can comprise centrifugal seal spare, and it is configured to move towards described the first turbine stage or described the second turbine stage, thereby when when described multi-stage turbine run duration produces radial centrifugal force, stoping radial leakage.Described interstage seal assembly comprises one or more sealing teeth, and it is configured to stop the inter-stage axial leakage occurs between described the first turbine stage and described the second turbine stage.Described interstage seal assembly comprises one or more cooling channels, and it is configured to guide cooling fluid to flow to described a plurality of the first blade sections or described a plurality of the second blade sections.Described system can comprise the interstage seal assembly that is arranged between described the first turbine stage and described the second turbine stage, and wherein said interstage seal assembly comprises a plurality of interstage seal assemblies.
In a second embodiment, a kind of system provided by the invention comprises the inter-stage turbine seal, and described inter-stage turbine seal is configured to axially be installed between first turbine stage and the second turbine stage of multi-stage turbine.Described inter-stage turbine seal comprises the inclination ribs, described inclination ribs be configured so that interstage seal assembly towards with pivot away from the axial axis of multi-stage turbine, and need not to dismantle the first impeller of described the first turbine stage and the second impeller of described the second turbine stage.
Described inclination ribs is oriented with the interior bridge portion of described inter-stage turbine seal and becomes certain angle, and wherein said inclination ribs makes the described inter-stage turbine seal can be towards pivoting with described axial axis away from described multi-stage turbine.Described inter-stage turbine seal comprises second recess part adjacent with described inclination ribs, described the second recess part is configured to take in the second portion of described the second impeller, thereby make described inter-stage turbine seal can towards with pivot away from described axial axis, and the first recess part of described inter-stage turbine seal is configured at described inter-stage turbine seal along described axial axis is taken in described the first impeller when described the first turbine stage moves first portion.Described inter-stage turbine seal comprises the first support feature, it is configured to cooperate with the second support feature on the part that is arranged at the blade sections that is connected to described the second impeller, thereby can stop described inter-stage turbine seal during the described inter-stage turbine seal of installation or removal, to move radially towards the axial axis of described multi-stage turbine, and can stop described inter-stage turbine seal circumferentially mobile around described axial axis at described multi-stage turbine run duration.
In the 3rd embodiment, a kind of method provided by the invention comprises: the first recess part of placing interstage seal assembly around the first wheel rim of turbo machine; The second recess part of described interstage seal assembly is pivoted towards the axial axis of described turbo machine; And move described interstage seal assembly along described axial axis towards the second wheel rim of described turbo machine, around described the second wheel rim described the second recess part to be set.
Described method comprises that further near the first support feature that makes described the first recess part that is arranged on described interstage seal assembly cooperates with the second support feature on the part that is arranged at the blade sections that is connected to described the first wheel rim, stoping described interstage seal assembly during the described interstage seal assembly of installation or removal, to move radially towards the described axial axis of described turbo machine, and can stop described interstage seal assembly circumferentially mobile around described axial axis at described turbo machine run duration.
Description of drawings
After consulting accompanying drawing and specifying below reading, can understand better these and other features of the present invention, aspect and advantage, in the accompanying drawings, similar similar part in the symbology institute drawings attached, wherein:
Fig. 1 is an embodiment's the schematic flow diagram of the gas turbine engine that can use turbine seal;
Fig. 2 embodiment's that to be gas turbine engine shown in Figure 1 intercept along the longitudinal axis side cross-sectional view;
Fig. 3 is the partial side view in cross section of gas turbine engine shown in Figure 2, illustrates an embodiment of the sealing configuration between the turbine stage;
Fig. 4 is the partial side view in cross section of gas turbine engine shown in Figure 2, illustrates an embodiment of the sealing configuration that pivots between adjacent level;
Fig. 5 is the partial side view in cross section of gas turbine engine shown in Figure 2, illustrates between adjacent level an embodiment of the sealing configuration that moves along the longitudinal axis;
Fig. 6 is the partial side view in cross section of gas turbine engine shown in Figure 2, illustrates an embodiment of the sealing configuration that is installed between the adjacent level;
Fig. 7 is an embodiment's of sealing configuration front perspective view;
Fig. 8 is an embodiment's of sealing configuration rear perspective view;
Fig. 9 is an embodiment's of sealing configuration front view; And
Figure 10 is an embodiment's of sealing configuration side view.
The component symbol tabulation:
Embodiment
Below will introduce one or more specific embodiment of the present invention.In order to briefly introduce these embodiments, may not can in the specification introduce all features of actual embodiment.Should be appreciated that, when in any engineering or design object, developing any this type of actual embodiment, all should work as the various decisions made from the embodiment certain relevant, to realize developer's specific objective, for example, whether to observe with System Dependent and with the restriction of traffic aided, these restrictions may be different because of the difference of embodiment.In addition, should be appreciated that, this type of exploitation is complicated and time consumption very, in any case but for benefiting from the those skilled in the art of this disclosure, this type of exploitation is still conventional design, construction and manufacturing operation.
When introducing the element of various embodiments of the invention, " one " and " described " are intended to expression one or more elements.Term " comprises ", " comprising " and " having " be intended to expression comprising property implication, and expression may also have other elements except listed element.
The present invention relates to comprise the gas turbine engine of interstage seal assembly, wherein each inter-stage Sealing comprises and need not to use additional components, spaced wheel for example, the just feature in salable inter-stage gap.Therefore, compare with the motor that uses spaced wheel, comprise that the gas turbine engine cost of this type of interstage seal assembly may be lower.For example, described gas turbine engine can comprise: the first turbine stage, and it comprises the first impeller, described the first impeller has a plurality of the first blade sections that circumferentially are distributed in around described the first impeller; And second turbine stage, it comprises the second impeller, described the second impeller has a plurality of the second blade sections that circumferentially are distributed in around described the second impeller.Interstage seal assembly can extend axially between described the first turbine stage and described the second turbine stage, with sealing inter-stage gap.In addition, each embodiment of described interstage seal assembly can mount and dismount in the situation of the rotor of not removing gas turbine engine.For example, described interstage seal assembly can be configured to carry out installation or removal when described the first impeller and the second impeller remain in original position in corresponding the first turbine stage and the second turbine stage.Therefore, as long as replace interstage seal assembly, just need not to disturb the rotor of gas turbine engine, thereby can reduce maintenance time, complexity, and/or cost.In further embodiment, described interstage seal assembly can comprise the inclination ribs, and described inclination ribs is configured so that described interstage seal assembly towards pivoting with axial axis away from combustion gas turbine, and need not to dismantle the first impeller or the second impeller.In other words, the pivot of interstage seal assembly can be in the situation that do not disturb rotor assembly to replace described interstage seal assembly.In other embodiments, the recess part of interstage seal assembly can be configured so that described interstage seal assembly pivots.
Fig. 1 is the block diagram of example system 10, and described system comprises the gas turbine engine 12 that can use interstage seal assembly, and described interstage seal assembly is configured to not carry out installation or removal in the situation that remove rotor, following will the detailed description in detail.In certain embodiments, system 10 can comprise aircraft, watercraft, locomotive, power generation system, or above combination.Shown in gas turbine engine 12 comprise induction part 16, compressor 18, firing chamber part 20, turbo machine 22, and discharge portion 24.Turbo machine 22 is connected to compressor 18 via axle 26.
As shown by arrows, air enters gas turbine engine 12 via induction part 16, then flows in the compressor 18, after compressing in compressor 18, enters firing chamber part 20.Shown in firing chamber part 20 comprise combustor outer casing 28, described combustor outer casing with one heart or the mode that circularizes be arranged to around the axle 26 between compressor 18 and the turbo machine 22.Pressurized air enters the firing chamber 30 from compressor 18, and in described firing chamber 30, pressurized air can and burn with fuel mix, thereby drives turbo machine 22.
Hot combustion gas flows through turbo machine 22 from firing chamber part 20, thereby via axle 26 drive compression machines 18.For example, combustion gas can apply power to turbine rotor blade turbo machine 22 is interior, so that axle 26 rotates.After flowing through turbo machine 22, hot combustion gas can be discharged from gas turbine engine 12 by discharge portion 24.As described below, turbo machine 22 can comprise a plurality of interstage seal assemblies, and described interstage seal assembly can be at the rotary component of turbo machine 22, and for example impeller carries out installation or removal when remaining in original position.Therefore, can in the situation that do not remove turbo machine 22 fully, interstage seal assembly be safeguarded.
Fig. 2 embodiment's that to be gas turbine engine 12 shown in Figure 1 intercept along the longitudinal axis 32 side cross-sectional view.As shown in the figure, combustion gas turbine 22 comprises three independent levels 34.Each grade 34 comprises the one group of blade 36 that is connected to impeller of rotor 38, and described impeller of rotor is connected to axle 26 (Fig. 1) in rotatable mode.Blade 36 extends radially outwardly from impeller of rotor 38, and part is arranged in the path of hot combustion gas.Sealing 40 extends between adjacent rotor impeller 38 and by its support.As described below, Sealing 40 can comprise recess part, described recess part be assemblied in adjacent impeller 38 around be used for to support.Described recess part can be configured so that Sealing 40 during installation or removal towards with pivot away from the longitudinal axis 32.Therefore, can be when impeller of rotor 38 remain in original position in the gas turbine engine 12, installation or removal Sealing 40.In addition, Sealing 40 can be used for cooling that level 34 is improved.Although described combustion gas turbine 22 is triple turbine, the Sealing 40 described in this specification can be used for having the turbo machine of any suitable type of the level of arbitrary number and axle.For example, Sealing 40 can be located at the single gas turbine machine, comprise two turbine systems of low-pressure turbine and high pressure turbine, or in the steam turbine.In addition, the Sealing 40 described in this specification also can be used for rotary compressor, for example, and compressor 18 shown in Figure 1.Sealing 40 can be made by different refractory alloys, such as but not limited to, nickel-base alloy.
As above described with reference to figure 1, air enters by induction part 16 and is compressed by compressor 18.Then, pressurized air enters firing chamber part 20 from compressor 18, described in firing chamber part 20, described pressurized air and fuel mix.The usually burning in firing chamber part 20 of the mixture of pressurized air and fuel, thereby the combustion gas of generation High Temperature High Pressure are to be used at turbo machine 22 interior generation moments of torsion.Particularly, described combustion gas apply power to blade 36, with wheel rotor 38.In certain embodiments, pressure drop can occur in 34 places at different levels of turbo machine 22, and it is so that by improper path the gas leakage current occurs.For example, described hot combustion gas can infiltrate the inter-stage volume between the turbine wheel 38, produces thermal stress thereby make on each parts of turbo machine.In certain embodiments, the inter-stage volume can be with discharging from compressor or being cooled off by the exhaust that another source provides.But flowing into described inter-stage volume, hot combustion gas can reduce cooling effect.Therefore, Sealing 40 can be arranged between the adjacent impeller 38, with volume between sealing and enclosure class, thus isolated hot combustion gas.In addition, Sealing 40 can be configured to cooling fluid is directed to described inter-stage volume, or cooling fluid is guided towards blade 36 from described inter-stage volume.
Fig. 3 is an embodiment's of a pair of adjacent rotor level 34 shown in Figure 2 side cross-sectional view.In the following discussion, can with reference to respect to the longitudinal axis 32 of gas turbine engine 12 axially or axle 50, radially or axle 52, and circumferentially or axle 54.Hot fluid, for example hot combustion gas or steam enter and 60 discharges in the downstream side at upstream side 58 by stream 56 (usually as shown by arrows).For purpose of explanation, Fig. 3 only illustrates the part of level 34.Particularly, shown in the first turbine stage 62 near upstream side 58, and shown in the second turbine stage 64 near downstream side 60.The first turbine stage 62 comprises the first impeller 66, and described the first impeller has a plurality of first blade sections 68 of extending from first round post part 70 radially outwards 52 of the first impeller 66.First round post part 70 is along the circumference setting of the first impeller 66, and comprises groove 72 (for example, axially dowetailed housing joint), is used for fixing the hypomere (for example, axially dovetail key shape thing 73) of the first blade sections 68.Similarly, the second turbine stage 64 comprises the second impeller 74, and described the second impeller has from second of the second impeller 74 takes turns a plurality of the second blade sections 76 that post part 78 radially outwards 52 extend.Second takes turns post part 78 along the circumference setting of the second impeller 74, and comprises groove 80 (for example, axial dowetailed housing joint), is used for the hypomere (for example, axial dovetail key shape thing 81) of fixing a plurality of the second blade sections 76.In certain embodiments, about 50 to 150 the first blade sections 68 and the second blade sections 76 can be installed, and it can be distributed in the first impeller 66 and the second impeller 74 and corresponding running shaft (usually extending in the direction shown in the arrow 50) on every side along circumferential 54.In further embodiment, except groove recited above and key shape thing, also can use additive method that the first blade sections 68 and the second blade sections 76 are connected to the first impeller 66 and the second impeller 74.
In certain embodiments, labyrinth seal part (labyrinth seal) 100 can be arranged on the position adjacent with interstage seal assembly 40, and between the first turbine stage 62 and the second turbine stage 64.Labyrinth seal part 100 can be configured to help to stop hot combustion gas 56 axial leakages.For example, labyrinth seal part 100 can comprise and is positioned at it towards the lip-deep wearing and tearing coating 102 of interstage seal assembly 40.Therefore, interstage seal assembly 40 can comprise and being arranged on and the one or more teeth 104 that wear and tear coating 102 adjacent positions.At gas turbine engine 10 run durations, tooth 104 can be very near wearing and tearing coating 102, thereby helps to stop hot combustion gas 56 axial leakage between the first turbine stage 62 and the second turbine stage 64.In response to transition (transient) condition, for example rotor transition, wearing and tearing coating 102 can be configured to partly wear and tear when contacting with tooth 104, thereby helps to prevent from damaging tooth 104.In other words, wearing and tearing coating 102 comparable tooth 104 softnesses.In further embodiment, the Sealing except labyrinth seal part 100 can use with interstage seal assembly 40.
The part that outer bridge portion 82 extends through intermediate support 86 and inclination ribs 88 can be described as end portion.Particularly, outer bridge portion 82 can comprise first end section 106 and second end section 108.In certain embodiments, first end section 106 and second end section 108 can comprise optional centrifugal seal spare 110, thereby help to stop hot combustion gas 56 radial leakages.For example, first end section 106 and second end section 108 can comprise groove 111, in order to cooperate with centrifugal seal spare 110.Sealing 110 can comprise: strut 112, arc supporting element 114, and seal bar 116.The strut 112 of centrifugal seal spare 110 can be assemblied in the groove 111.Arc supporting element 114 can be connected to strut 112.At last, seal bar 116 can be connected to the end of arc supporting element 114.When gas turbine engine 10 operation, centrifugal force can make seal bar 116 away from interstage seal assembly 40 and mobile towards those surfaces of interstage seal assembly 40 towards the first turbine stage 62 and the second turbine stage 64.Therefore, at gas turbine engine 10 run durations, seal bar 116 can contact with the second blade sections 76 with the first blade sections 68, thereby helps to stop hot combustion gas 56 radial leakages.In order to adapt to the movement of centrifugal seal spare 110 at gas turbine engine 10 run durations, can there be little gap between the first end section 106 of interstage seal assembly 40 and the second end section 108 and between the first turbine stage 62 and the second turbine stage 64.By towards or move away from interstage seal assembly 40, centrifugal seal spare 110 can keep contacting with the second turbine stage 64 with the first turbine stage 62, though may make the gap gas turbine engine 10 run durations increase or the axial transient period that reduces between also be like this.In other embodiments, centrifugal seal spare 110 can omit, and perhaps the Sealing except centrifugal seal spare 110 can be used on outer bridge portion 82 places, to carry out radial seal.
In certain embodiments, second end section 108 can comprise the first support feature 118, its be configured to be arranged on one or more the second blade sections 76 on the second support feature 120 cooperate.For example, the first support feature 118 can negative alignment portion (for example, recess), and the second support feature 120 can positive alignment portion (for example, key shape thing).In other embodiments, the first support feature 118 can positive alignment portion, and the second support feature 120 can negative alignment portion.During installation or removal interstage seal assembly 40, the first support feature 118 and the second support feature 120 can help to stop interstage seal assembly 40 to move radially towards the axial axis 50 of gas turbine engine 10 on direction 52 altogether jointly.In addition, at gas turbine engine 10 run durations, the first support feature 118 and the second support feature 120 can help to stop interstage seal assembly 40 circumferentially mobile on direction 54.Below will be described in detail in during the installation and removal interstage seal assembly 40 use of the first support feature 118 and the second support feature 120.
In described embodiment, interstage seal assembly 40 to be to circularize mode setting (on circumferential 54) between the first impeller 66 and the second impeller 74, and wherein inter-stage seal section 41 is sections of assembly 40.Therefore, the first impeller 66 and the second impeller 74 form loop configuration, and wherein interstage seal assembly 40 extends between the first impeller 66 and the second impeller 74 as loop configuration.At run duration, the first impeller 66 and the second impeller 74 and interstage seal assembly 40 rotate around common shaft.Interstage seal assembly 40 can comprise segmentation (for example, 2 to the 100 sections) loop configuration of 360 degree, and it is connected to the first adjacent impeller 66 and the second impeller 74, forming the wall of volume between hot isolation level or impeller cavity 134, thereby forms aircooling cabinet.
Fig. 4 is to Figure 6 shows that each step that can carry out during interstage seal assembly 40 is installed.Carry out conversely just detachable interstage seal assembly 40 of these steps.From first step, Figure 4 shows that the partial side view in cross section of the interstage seal assembly 40 that between the first turbine stage 62 and the second turbine stage 64, pivots.As shown in Figure 4, dismantle the second blade sections 76, thereby helped to install interstage seal assembly 40.The first blade sections 68 remains in the original position in the first order 62.In other embodiments, by dismantling the first blade sections 68 interstage seal assembly 40 is installed, wherein the second blade sections 76 remains in the original position in the second level 64.Therefore, interstage seal assembly 40 is installed can not need be dismantled the first blade sections 68 and the second blade sections 76, thereby simplify substantially the installation or removal of interstage seal assembly 40.In addition, as shown in Figure 4, the first impeller 66 and the second impeller 74 remain in original position during (and dismounting) interstage seal assembly 40 is installed, thereby simplify substantially the installation or removal of interstage seal assembly 40.During interstage seal assembly 40 is installed, second end section 126 is arranged or is hooked in the below of the second wheel rim 132.Particularly, make the angle 148 and the 132 adjacent settings of the second wheel rim that form between inclination ribs 88 and the interior bridge portion 84, and overlapping with described the second wheel rim.In other words, the lap 149 of angle 148 and the second wheel rim 132 is positioned on axial 50 and radially 52.Therefore, interstage seal assembly 40 can pivot or rotation towards axial axis 50 on the direction of arrow 150 around angle 148.As shown in Figure 4, when interstage seal assembly 40 when direction 150 moves, the outward edge 151 of first end section 124 can move along arc 152.Therefore, when interstage seal assembly 40 when axial axis 50 pivots, lap 149 provides sufficient gap, so that outward edge 151 is crossed (clear) first wheel rim 128.When installation process began, inclination ribs 88 can be parallel to the second surface 153 of taking turns post part 78 substantially.The configuration of inclination ribs 88 and recess part 90 makes described lap 149 become large, thereby makes outward edge 151 cross the first wheel rim 128, shown in dotted line 152.In addition, from sectional view, inclination supporting part 90 can be overlapping with the part 154 of the second wheel support upright 78.As hereinafter describing in detail, two or more supporting parts 90 can arrange around the second wheel support upright 78.Along with the continuation that interstage seal assembly 40 processes are installed, rotate towards the first wheel rim 128 first end section 124, and inclination ribs 88 moves away from the second wheel support upright 78.
Fig. 5 is the partial side view in cross section of the interstage seal assembly 40 that moves along axial axis 50.As shown in Figure 5, interstage seal assembly 40 has rotated, like this, just first end section 124 can below the first wheel rim 128, move, shown in arrow 170.In addition, second end section 126 can keep overlapping with the second wheel rim 132.Particularly, angle 148 can be adjacent with the second wheel rim 132.Lap 149 makes first end section 124 mobile below the first wheel rim 128, and lap 149 remains between second end section 126 and the second wheel rim 132 simultaneously.When interstage seal assembly 40 when the direction of arrow 170 moves, axially stop member 130 can contact the first wheel rim 128, thereby stops interstage seal assembly 40 further to move axially 50.In addition, angle 148 is at least part of moves away from the second wheel rim 132.
Fig. 6 is the partial side view in cross section of interstage seal assembly 40, is illustrated as to finish installation process.As shown in Figure 6, axially stop member 130 is adjacent with the first wheel rim 128, and angle 148 is removed away from the second wheel rim 132.It is 50 overlapping vertically with the first wheel rim 128 that first end section 124 keeps, and second end section 126 keeps 50 overlapping vertically with the second wheel rim 132.In addition, the second blade sections 76 can move towards interstage seal assembly 40 on the direction of arrow 180.Particularly, the second support feature 120 can cooperate with the first support feature 118.In case the first support feature 118 with after the second support feature 120 cooperates, can stop interstage seal assembly 40 towards or move away from the axial axis 50 of gas turbine engine 10.Therefore, interstage seal assembly 40 can the oneself be supported (self-supporting) in the installation process of remainder, and need not fixing or restriction interstage seal assembly 40 moves.At last, labyrinth seal part 100 can move towards interstage seal assembly 40 on the direction of arrow 182.In certain embodiments, labyrinth seal part 100 can be connected to the shell of gas turbine engine 10, and therefore, labyrinth seal part 100 can be installed when the shell of gas turbine engine 10 is installed.After gas turbine engine 10 started, centrifugal seal spare 110 (if you are using) can outwards move, so that radial seal is carried out in the gap between interstage seal assembly 40 and the first turbo machine 62 and the second turbo machine 64.
Fig. 7 is an embodiment's the front perspective view of an inter-stage seal section 41 of interstage seal assembly 40.As shown in Figure 7, axially stop member 130 comprises first surface 200 and second surface 202.First surface 200 can be towards the first turbine stage 62, and second surface 202 can be towards interstage seal assembly 40.In certain embodiments, first surface 200 is normally smooth, with corresponding to the first impeller 66.In addition, second surface 202 is flexible, thereby 124 connection provides larger support to the first end section for axial stop member 130.In other embodiments, second surface 202 can be smooth.In addition, axially stop member 130 can have width 204, and described width width about and inter-stage seal section 40 is roughly the same.In addition, axially stop member 130 can be provided with height 206, and described height can be through selecting to think that axial stop member 130 provides enough surface areas, thereby helps to stop moving axially that interstage seal assembly 40 do not expect.
Fig. 8 is an embodiment's the rear perspective view of an interstage seal assembly 40 of interstage seal assembly 41.As shown in Figure 8, interstage seal assembly 40 comprises two inclination supporting parts 90.Particularly, described two inter-stage supporting parts 90 are positioned on the outside 218 of interstage seal assembly 40.Therefore, there is inter-stage supporting part gap 220 between these two inclination supporting parts 90.During installation or removal interstage seal assembly 40, the second wheel support upright 78 can be assembled in the inter-stage supporting part gap 220.Therefore, during installation or removal interstage seal assembly 40, interstage seal assembly 40 can pivot around the second wheel support upright 78.By pivoting around the second wheel support upright 78, the second level 64 can remain in original position during safeguarding interstage seal assembly 40.In described embodiment, each supporting part 90 that tilts is provided with width 222.The width 222 of described inclination supporting part 90 altogether may be approximately identical with the width 204 of interstage seal assembly 40 with inter-stage supporting part gap 220.In addition, described inclination supporting part 90 can be provided with height 224.As shown in Figure 8, height 224 height less than interstage seal assembly 40.In other embodiments, height 224 may be smaller or greater, specifically depends on the support that the inclination amount of inclination ribs 88 and outer bridge portion 82 are required.For example, if angle 94 is less, the height 224 of the supporting part 90 that then tilts may be larger, thinks that outer bridge portion 82 provides extra support.In other embodiments, only have an inclination supporting part 90 be arranged at interstage seal assembly 40 near.In further embodiment, interstage seal assembly 40 can comprise two with the supporting part 90 that tilts.Some embodiment can omit inclination supporting part 90.
Fig. 9 is the front view of three adjacent interstage seal assemblies 40 of segmented interstage seal assembly 41.Assembly 41 can comprise a plurality of interstage seal assemblies 40,2 to 100 Sealings 40 for example, and it is arranged to adjacent one another are, to form around 360 degree unbroken loop of the longitudinal axis 32 of gas turbine engine 10.As shown in Figure 9, each interstage seal assembly 40 is arc circumferential 54.Assembly 41 with interstage seal assembly 40 can comprise outside seal may 240 and inner seal liner 242.Axial groove 246 can be formed in outer bridge portion 82 and the interior bridge portion 84, to hold outer axial Sealing 240 and interior axial seal 242.In other words, outside seal may 240 and inner seal liner 242 extend along axial groove 246 on axial 50.Outside seal may 240 and inner seal liner 242 can be installed in the interstage seal assembly 40 of aforesaid interstage seal assembly 41 between each Sealing.Outside seal may 240 and inner seal liner 242 can help to stop hot combustion gas 56 radial leakages.
Figure 10 is an embodiment's of interstage seal assembly 40 side view.As shown in figure 10, outside seal may 240 and inner seal liner 242 are arranged in the axial groove 246, and described axial groove extends along outer bridge portion 82 and interior bridge portion 84.In addition, interstage seal assembly 40 can comprise one or more cooling channels 260, so that cooling fluid flows towards the first blade sections 68 and the second blade sections 76.For example, in certain embodiments, cooling channel 260 can make cooling fluid flow towards the first blade sections 68 and the second blade sections 76 from inter-stage volume 134.In other embodiments, cooling fluid can flow to the first blade sections 68 and the second blade sections 76 by the shell mechanism of cooling channel 260 from gas turbine engine 10.Cooling channel 260 can be formed in outer bridge portion 82 and interior bridge portion 84, intermediate support beam 86 and/or the inclination ribs 88.The cooling channel 260 that is formed in outer bridge portion 82 and the interior bridge portion 84 can make cooling fluid flow to the first blade sections 68 and the second blade sections 76 from inter-stage volume 134 or shell mechanism.The cooling channel 260 that is formed in intermediate support beam 86 and/or the inclination ribs 88 can make cooling fluid flow between recess part 98 and Seal cage 96.
This specification has used various examples to disclose the present invention, comprises optimal mode, and any technician in field can put into practice the present invention under also allowing simultaneously, comprises and makes and use any device or system, and implement any method of containing.Protection scope of the present invention is defined by claims, and can comprise other examples that one of ordinary skill in the art find out.If the structural element of other these type of examples is identical with the letter of claims, if or the letter of the equivalent structure key element that comprises of this type of example and claims without essential difference, then this type of example also belongs to the scope of claims.
Claims (15)
1. system comprises:
Multi-stage turbine (22), it comprises:
The first turbine stage (62), it comprises the first impeller (66), described the first impeller has and circumferentially is distributed in described the first impeller (66) a plurality of the first blade sections (68) on every side;
The second turbine stage (64), it comprises the second impeller (74), described the second impeller has and circumferentially is distributed in described the second impeller (74) a plurality of the second blade sections (76) on every side; And
Interstage seal assembly (40), it extends axially between described the first turbine stage (62) and described the second turbine stage (64), and wherein said interstage seal assembly (40) is configured and can carries out installation or removal when described the first impeller (66) and described the second impeller (74) remain in original position in corresponding described the first turbine stage (62) and described the second turbine stage (64).
2. system according to claim 1, it is characterized in that, each blade sections in described a plurality of the first blade sections (68) uses a plurality of the first assembling sets (70) to be connected to described the first impeller (66), and each blade sections in described a plurality of the second blade sections (76) uses a plurality of the second assembling sets (78) to be connected to described the second impeller (74).
3. system according to claim 2, it is characterized in that, each first assembling set (70) comprises the first groove (72) of being located in described the first impeller (66) and is located in described a plurality of the first blade sections (68) first key shape thing (73) in the blade sections, and each second assembling set (78) comprises the second groove (80) of being located in described the second impeller (74) and is located in described a plurality of the second blade sections (76) the second key shape thing (81) in the blade sections.
4. system according to claim 1, it is characterized in that, described interstage seal assembly (40) is configured to can pivot towards the axial axis (50) of described multi-stage turbine (22) during described interstage seal assembly (40) is installed, and described interstage seal assembly (40) is configured to can pivot away from the described axial axis (50) of described multi-stage turbine (22) during the described interstage seal assembly of dismounting (40).
5. system according to claim 1, it is characterized in that, described interstage seal assembly (40) comprises the inclination ribs (88) that becomes certain angle (94) with the interior bridge portion (84) of described interstage seal assembly (40), wherein said inclination ribs (88) make described interstage seal assembly (40) can towards with axial axis away from described multi-stage turbine (22) pivot (50).
6. system according to claim 5, it is characterized in that, described interstage seal assembly (40) comprises second recess part (98) adjacent with described inclination ribs (88), described the second recess part (98) is configured to take in the second portion (132) of described the second impeller (74), so that described interstage seal assembly (40) can towards with pivot (150) away from described axial axis (50), and first recess part (98) of described interstage seal assembly (40) is configured at described interstage seal assembly (40) along described axial axis (50) is taken in described the first impeller (66) when described the first turbine stage (62) is mobile first portion (128).
7. system according to claim 5 is characterized in that, described angle (94) less than approximately 75 the degree.
8. system according to claim 1, it is characterized in that, described interstage seal assembly (40) comprises the first support feature (118), it is configured to and is arranged on described a plurality of the first blade sections (68), or the second support feature (120) on the one or more blade sections in described a plurality of the second blade sections (76) cooperates, to stop described interstage seal assembly (40) to move radially (52) towards the axial axis (50) of described multi-stage turbine (22) during the described interstage seal assembly of installation or removal (40), rainbow can stop described interstage seal assembly (40) circumferentially to move (54) at described multi-stage turbine (22) run duration around described axial axis (50).
9. system according to claim 8 is characterized in that, described the first support feature (118) comprises groove, and described the second support feature (120) comprises key shape thing.
10. system according to claim 1, it is characterized in that, described interstage seal assembly (40) comprises axial end part (124,126), and it is configured at described multi-stage turbine (22) run duration at the wheel rim (128,132) of (52) cooperation described first impeller (66) or described the second impeller (74) radially.
11. system according to claim 1, it is characterized in that, described interstage seal assembly (40) comprises centrifugal seal spare (110), it is configured to towards described the first turbine stage (62) or described the second turbine stage (64) mobile, thereby when when described multi-stage turbine (22) run duration produces radial centrifugal force, stoping radial leakage.
12. system according to claim 1, it is characterized in that, described interstage seal assembly (40) comprises one or more sealing teeth (104), and it is configured to stop the inter-stage axial leakage occurs between described the first turbine stage (62) and described the second turbine stage (64).
13. system according to claim 1, it is characterized in that, described interstage seal assembly (40) comprises one or more cooling channels (260), and it is configured to guide cooling fluid to flow to described a plurality of the first blade sections (68) or described a plurality of the second blade sections (76).
14. system according to claim 1, it is characterized in that, comprise the interstage seal assembly (41) that is arranged between described the first turbine stage (62) and described the second turbine stage (64), wherein said interstage seal assembly (41) comprises a plurality of interstage seal assemblies (40).
15. a system comprises:
Inter-stage turbine seal (40), it is configured to axially, and (50) are installed between first turbine stage (62) and the second turbine stage (64) of multi-stage turbine (22), wherein said inter-stage turbine seal (40) comprises inclination ribs (88), described inclination ribs is configured so that described inter-stage turbine seal (40) can be towards pivoting with axial axis (50) away from described multi-stage turbine (22), and need not to dismantle first impeller (66) of described the first turbine stage (62) and second impeller (74) of described the second turbine stage (64).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/163,418 US20120321437A1 (en) | 2011-06-17 | 2011-06-17 | Turbine seal system |
| US13/163,418 | 2011-06-17 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102852566A true CN102852566A (en) | 2013-01-02 |
Family
ID=46245938
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012102017506A Pending CN102852566A (en) | 2011-06-17 | 2012-06-15 | Turbine seal system |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20120321437A1 (en) |
| EP (1) | EP2535523A2 (en) |
| CN (1) | CN102852566A (en) |
Cited By (4)
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|---|---|---|---|---|
| CN104061594A (en) * | 2013-03-21 | 2014-09-24 | 通用电气公司 | Transition duct with improved cooling in turbomachine |
| CN108603806A (en) * | 2016-01-27 | 2018-09-28 | 赛峰飞机发动机公司 | The turbine testboard of rotary part including the component for turbine testboard or for turbine and the method for using the testboard |
| CN110273712A (en) * | 2018-03-14 | 2019-09-24 | 通用电气公司 | Chamber purges pipeline between grade |
| CN113891984A (en) * | 2019-05-29 | 2022-01-04 | 赛峰飞机发动机公司 | Dynamic seal for a turbomachine comprising a multilayer wear-resistant component |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014100316A1 (en) * | 2012-12-19 | 2014-06-26 | United Technologies Corporation | Segmented seal for a gas turbine engine |
| US10287905B2 (en) | 2013-11-11 | 2019-05-14 | United Technologies Corporation | Segmented seal for gas turbine engine |
| US9915204B2 (en) * | 2014-06-19 | 2018-03-13 | United Technologies Corporation | Systems and methods for distributing cooling air in gas turbine engines |
| EP2995778B1 (en) * | 2014-09-12 | 2020-10-28 | United Technologies Corporation | Method and assembly for reducing secondary heat in a gas turbine engine |
| US10662793B2 (en) * | 2014-12-01 | 2020-05-26 | General Electric Company | Turbine wheel cover-plate mounted gas turbine interstage seal |
| US10634055B2 (en) | 2015-02-05 | 2020-04-28 | United Technologies Corporation | Gas turbine engine having section with thermally isolated area |
| US9920652B2 (en) | 2015-02-09 | 2018-03-20 | United Technologies Corporation | Gas turbine engine having section with thermally isolated area |
| US10337345B2 (en) | 2015-02-20 | 2019-07-02 | General Electric Company | Bucket mounted multi-stage turbine interstage seal and method of assembly |
| DE102016215983A1 (en) | 2016-08-25 | 2018-03-01 | Siemens Aktiengesellschaft | Rotor with split sealing ring |
| EP3287595A1 (en) | 2016-08-25 | 2018-02-28 | Siemens Aktiengesellschaft | Rotor with segmented sealing ring |
| US11519286B2 (en) * | 2021-02-04 | 2022-12-06 | General Electric Company | Sealing assembly and sealing member therefor with spline seal retention |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2691749B1 (en) * | 1992-05-27 | 1994-07-22 | Snecma | SEALING DEVICE BETWEEN STAGES OF BLADES AND A TURNING DRUM IN PARTICULAR TO AVOID LEAKS AROUND THE STAGES OF RECTIFIER BLADES. |
| FR2825748B1 (en) * | 2001-06-07 | 2003-11-07 | Snecma Moteurs | TURBOMACHINE ROTOR ARRANGEMENT WITH TWO BLADE DISCS SEPARATED BY A SPACER |
| US6558118B1 (en) * | 2001-11-01 | 2003-05-06 | General Electric Company | Bucket dovetail bridge member and method for eliminating thermal bowing of steam turbine rotors |
| US6761529B2 (en) * | 2002-07-25 | 2004-07-13 | Mitshubishi Heavy Industries, Ltd. | Cooling structure of stationary blade, and gas turbine |
| GB2438858B (en) * | 2006-06-07 | 2008-08-06 | Rolls Royce Plc | A sealing arrangement in a gas turbine engine |
| US20090238683A1 (en) * | 2008-03-24 | 2009-09-24 | United Technologies Corporation | Vane with integral inner air seal |
-
2011
- 2011-06-17 US US13/163,418 patent/US20120321437A1/en not_active Abandoned
-
2012
- 2012-06-12 EP EP12171671A patent/EP2535523A2/en not_active Withdrawn
- 2012-06-15 CN CN2012102017506A patent/CN102852566A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104061594A (en) * | 2013-03-21 | 2014-09-24 | 通用电气公司 | Transition duct with improved cooling in turbomachine |
| CN104061594B (en) * | 2013-03-21 | 2018-02-23 | 通用电气公司 | The transition conduit of improved cooling is carried in turbine |
| CN108603806A (en) * | 2016-01-27 | 2018-09-28 | 赛峰飞机发动机公司 | The turbine testboard of rotary part including the component for turbine testboard or for turbine and the method for using the testboard |
| CN108603806B (en) * | 2016-01-27 | 2020-06-16 | 赛峰飞机发动机公司 | Rotating part for a turbine test bench or for a turbomachine, turbine test bench comprising said part and method of using said test bench |
| CN110273712A (en) * | 2018-03-14 | 2019-09-24 | 通用电气公司 | Chamber purges pipeline between grade |
| CN113891984A (en) * | 2019-05-29 | 2022-01-04 | 赛峰飞机发动机公司 | Dynamic seal for a turbomachine comprising a multilayer wear-resistant component |
Also Published As
| Publication number | Publication date |
|---|---|
| US20120321437A1 (en) | 2012-12-20 |
| EP2535523A2 (en) | 2012-12-19 |
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Application publication date: 20130102 |