CN101660431A - System and method for adjusting clearance in a gas turbine - Google Patents
System and method for adjusting clearance in a gas turbine Download PDFInfo
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- CN101660431A CN101660431A CN200910172097A CN200910172097A CN101660431A CN 101660431 A CN101660431 A CN 101660431A CN 200910172097 A CN200910172097 A CN 200910172097A CN 200910172097 A CN200910172097 A CN 200910172097A CN 101660431 A CN101660431 A CN 101660431A
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- elongated element
- turbine cylinder
- turbine
- cover assembly
- guard shield
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a system and a method for adjusting clearance in a gas turbine. A system (10) for adjusting a clearance in a gas turbine including a turbine rotor (16) and a plurality of buckets (39) is disclosed. The system (10) includes: a shroud assembly (30) including at least one shroud segment (31), the at least one shroud segment (31) being disposed in an interior of a turbine shell (12); and an elongated member (32) extending from the turbine shell (12). The at least one shroud segment (31) is attached to an end of the elongated member (32), the elongated member (32) configured to move in response to a temperature change to move the shroud segment and change a clearance between the shroud segment (31) and at least one of the plurality of buckets (39).
Description
Technical field
[0001] theme disclosed herein relates to gas turbine, and more specifically, relates to the method and system that is used to regulate wheel blade or vane tip and is connected to the gap between the cover assembly on the turbine cylinder.
Background technique
[0002] in order to raise the efficiency, gas turbine (for example be used for generating electricity or aviation those) uses the turbo machine " guard shield " that is arranged in the turbine cylinder.Compare with the gap between wheel blade top and the turbine cylinder, guard shield provides the gap that reduces between top that is arranged on the wheel blade on the turbine rotor and guard shield.The gap that reduces like this provides the efficient of raising by unwanted " leakage " with the hot gas on the top that prevents wheel blade in the threshold value gap that keeps between the top of guard shield and wheel blade reducing.The gap that increases may cause gas leakage, and this gas leakage may reduce turbine efficiency.
[0003] current shield system adopts the independent segmented guard shield that is connected on the turbine cylinder and is kept together by for example turbine casing hook.Gap between wheel blade top and the guard shield is only driven by the thermal time constant behavior between turbine cylinder and the rotor/wheel blade.Initial wheel blade top/guard shield gap can be set enough highly, to prevent friction, still can not control such gap on one's own initiative under transient state or equilibrium condition.Wheel blade/the guard shield of turbine cylinder out of roundness and transient state rubs, and both play an important role in the stable state gap that increases.The gap that low temperature is set up, promptly the gap of setting before operation can be set enough highly, and to alleviate friction, still in fact, this will make the stable state gap increase, and reduce engine efficiency and output thus.Therefore, need be used for the wheel blade top of control gas turbine during the transient state of for example turbo machine and/or steady-state operation and the improved system and method in the gap between the guard shield.
Summary of the invention
[0004] exemplary embodiment according to the present invention system structure, that be used for regulating the gap of the gas turbine that comprises turbine rotor and a plurality of wheel blades comprises: comprise the cover assembly of at least one sheath section, this at least one sheath section is arranged in the inside of turbine cylinder; And the elongated element that extends from turbine cylinder.This at least one sheath section is attached on the end of elongated element, and this elongated element is configured to so that move in response to temperature variation, with mobile sheath section and change sheath section and a plurality of wheel blade at least one between the gap.
[0005] other exemplary embodiment of the present invention comprises the method for regulating the gap in the gas turbine that comprises turbine rotor and a plurality of wheel blades.This method comprises: cover assembly is arranged on the turbine cylinder, and this cover assembly comprises the sheath section on the end that is attached to elongated element; Elongated element is extended from turbine cylinder, and sheath section is arranged in the inside of turbine cylinder; And thermal source is applied to cover assembly, so that sheath section moves, and change gap between in sheath section and this a plurality of wheel blades at least one.
[0006] technology by exemplary embodiment of the present invention has realized additional features and advantage.This paper describes in detail other embodiments of the invention and aspect, and it is considered as the part of claimed invention.In order to understand the present invention and advantage thereof and feature better, referring to describing and accompanying drawing.
Description of drawings
[0007] Fig. 1 is the perspective view according to the gas turbine of one exemplary embodiment of the present invention;
[0008] Fig. 2 is the side view that is connected to an exemplary embodiment of the cover assembly on the gas turbine of Fig. 1;
[0009] Fig. 3 is the side view of another exemplary embodiment of the cover assembly of Fig. 2;
[0010] Fig. 4 be Fig. 2 cover assembly another exemplary embodiment axially and the side direction view;
[0011] Fig. 5 be Fig. 2 cover assembly another exemplary embodiment axially and the side direction view, it comprises the example values that is used for the gap between guard shield and the turbine cylinder;
[0012] Fig. 6 is the side view of another exemplary embodiment of the cover assembly of Fig. 2;
[0013] Fig. 7 is the side view of another exemplary embodiment of the cover assembly of Fig. 2;
[0014] Fig. 8 is the side view of another exemplary embodiment of the cover assembly of Fig. 2;
[0015] Fig. 9 is the side view of another exemplary embodiment of the cover assembly of Fig. 2;
[0016] Figure 10 is the axial view of an exemplary embodiment of cooling construction of the cover assembly of Fig. 2;
[0017] Figure 11 is the axial view of another exemplary embodiment of the cooling construction of Figure 10;
[0018] Figure 12 is the axial view of another exemplary embodiment of the cooling construction of Figure 10;
[0019] Figure 13 is the explanation that is used for controlling the system in the guard shield of gas turbine and the gap between the wheel blade top; And
[0020] Figure 14 has provided the flow chart of a kind of illustrative methods in the guard shield that is used for controlling gas turbine and the gap between the wheel blade top.
List of parts:
| Gas Turbine Modules | ??10 |
| Turbine cylinder | ??12 |
| Compressor | ??14 |
| Power turbine | ??16 |
| Rotor | ??18 |
| The firing chamber | ??20 |
| Rotor blade or wheel blade | ??39 |
| Cover assembly | ??30 |
| Sheath section | ??31 |
| Elongated element | ??32 |
| Interior guard shield | ??40 |
| Outer wall | ??42 |
| Pipe | ??44 |
| Projection | ??46 |
| Electric heater | ??48 |
| Outer shield | ??34 |
| Inwall | ??36 |
| Middle guard shield | ??38 |
| Inlet (pipeline) | ??50 |
| Controlling mechanism | ??52 |
| Heat insulator | ??54 |
| Lid | ??56 |
| Positioning means | ??58 |
| Pumping system | ??60 |
| The elongated element pipeline | ??64 |
| Pin | ??66 |
| Pipeline | ??64 |
| Stablize projection | ??68 |
| Lock feature (lid) | ??70 |
| Alignment feature | ??71 |
| Pin in addition | ??72 |
| The guard shield pipeline | ??74 |
| Cooling source | ??78 |
| Cavity | ??80 |
| Control system | ??90 |
| Computer | ??91 |
| Displacement transducer | ??92 |
| Method | ??100 |
| Step | ??101-104 |
Embodiment
[0021] provides a kind of system and method that is used for making the member displacement of turbo machine or other system.This system comprises and being configured to so that the parts that mobile heat is actuated in response to temperature variation.In one embodiment, the thermal expansion coefficient (" CTE ") of this heat parts of actuating is different with the CTE of the one or more structures that are attached to it.A kind of method is provided, and this method comprises the parts that the heating or the heat of cooling are actuated, so that these parts move.In one embodiment, the parts that heat is actuated are elongated element, for example bar or cylinder.
[0022] in one embodiment, system comprises the parts that heat is actuated, the parts that this heat is actuated are connected on turbine cylinder or other main body at place, an end, and on place, the other end is connected to such as movable members such as turbomachine shrouds, to regulate in wheel blade top on the gas turbine and the gap between one or more guard shield.Though this paper has described the wheel blade top, this system can use with wheel blade, the blade of any kind or other device that is used to turbine rotor is moved.This paper is described as general cylindrical post or pipe with elongated element, but elongated element can be and has any suitable shape of certain size in the radial direction.As used herein, term " radially " is meant from the spin axis of the center of turbine rotor or turbine rotor and extends and perpendicular to the direction of the main axis or the spin axis of turbine rotor.Though the parts that this paper actuates heat in conjunction with turbine assembly are described, the parts that can use heat to actuate in conjunction with any system or equipment of the displacement that utilizes member.
[0023], shown Gas Turbine Modules substantially at 10 places according to one exemplary embodiment of the present invention structure referring to Fig. 1.Gas Turbine Modules 10 is included in the turbine cylinder 12 that is held in place by around the compressor 14 of rotor 18 connections and the power turbine 16.Firing chamber 20 is formed between 16 sections in the compressor 14 of assembly 10 and the turbo machine.A plurality of rotor blades or wheel blade 39 are connected on the turbo machine 16 by for example rotor disk.Turbine cylinder 12 comprises a plurality of cover assemblies 30, and these a plurality of cover assemblies 30 are attached on the interior section of turbine cylinder 12 and define gap " C " between cover assembly 30 and wheel blade 39.
[0024] referring to Fig. 2, cover assembly 30 is arranged in the turbine cylinder 12.Cover assembly 30 comprises one or more sheath section 31, and wherein each sheath section is attached on the elongated element 32 removedly by any suitable mechanism (for example pin attachment or threaded attachment part).Elongated element 32 radially extends towards wheel blade 39 from turbine cylinder 12.Sheath section 31 separates with wheel blade 39, and (and) distance between the top of wheel blade 39 defines gap " C " between interior guard shield 40 and wheel blade top.Elongated element 32 has the thermal expansion coefficient (" CTE ") different with the thermal expansion coefficient (" CTE ") of turbine cylinder 12 and/or other member.In one embodiment, elongated element 32 has the CTE bigger than turbine cylinder 12.Elongated element 32 is inflatable and/or retractable by the temperature of selecting this elongated element, with the clearance C between control sheath section 31 and the wheel blade 39.
[0025] referring to Fig. 3, in one embodiment, elongated element 32 radially extends and should manage 44 by pipe 44-from outer wall 42 and forms by turbine cylinder 12 and projection 46 (for example lug boss).In one embodiment, the radial length of projection 46 is chosen as so that increase the radial length of elongated element 32, and increases or regulate the shift amount of elongated element 32 thus in response to variation of temperature.In this embodiment, projection 46 is made by the material with CTE higher than the CTE of elongated element 32 (for example alloy).In one embodiment, electric heater 48 is arranged to contact with projection 46, thereby makes and heat can be applied to elongated element 32 and/or projection 46, with the expansion of control elongated element 32 and/or projection 46.
[0026] in one embodiment, elongated element 32 has the thermal expansion coefficient (" CTE ") different with the thermal expansion coefficient (" CTE ") of projection 46 and/or turbine cylinder 12.For example, as shown in Figure 4, elongated element 32 has the CTE littler than the CTE of projection 46.By selecting the CTE of each member, the amount that guard shield 40 expands in can controlling with respect to the amount of applied heating or cooling.For example, because elongated element 32 has the CTE littler than the CTE of projection 46, so heat can be applied to projection 46, the displacement with control cover assembly 30 provides any important contribution and need not 32 pairs of displacements of elongated element.In one embodiment, elongated element 32 has enough low CTE, thereby makes that displacement is the result of heating projection 46 substantially.
[0027] referring to Fig. 4, another embodiment of cover assembly 30 is arranged in the turbine cylinder 12.In this embodiment, one or more sheath section 31 comprise elongated element 32 separately, be attached to outer shield 34 on the inwall 36 of turbine cylinder 12, be attached to the middle guard shield 38 on the elongated element 32, and the interior guard shield 40 on the guard shield 38 in the middle of being attached to.In one embodiment, middle guard shield 38 is attached on the elongated element removedly by any suitable mechanism (for example pin attachment or threaded attachment part).Interior guard shield 40 separates with wheel blade 39, and (and) distance between the top of wheel blade 39 defines the gap between interior guard shield 40 and wheel blade top.
[0028] in one embodiment, cover assembly 30 comprises any amount of section 31, and each section 31 comprises at least one elongated element 32 and the guard shield 34,38,40 at least one.In example shown in Figure 2, cover assembly 30 forms the ring shield with four quadrants.Each section 31 comprises an elongated element 32, outer shield 34, guard shield 38 and six interior guard shields 40 in the middle of one.The quantity and the size of the section 31 described in the embodiment of this paper, and the quantity of elongated element 32 and guard shield 34,38,40 is exemplary, and unrestricted.
[0029] in one embodiment, comprise inlet 50,, perhaps allow other heating or cooling source (entering) to allow from the air or the steam (entering) through heating of the inside of turbine cylinder 12.Such source can comprise air, gas and steam.
[0030] in one embodiment, fixing or controlling mechanism 52 is attached on the elongated element 32.Mechanism 52 can be connected on the projection 46, to allow removing elongated element 32 with manual mode or mechanically mobile elongated element 32 or from cover assembly 30.
[0031] in another embodiment, provide heat insulator 54,, and heating or cooling source can be applied to elongated element 32 via inlet 50 so that heat is isolated elongated element 32 and projection 46.Perhaps, this embodiment allows from the air of the inside of turbine cylinder 12 elongated element 32 to be remained under the specific temperature, thereby and by heat being applied to projection 46 and projection 46 is expanded reach to make elongated element 32 withdraw the elongated element 32 of withdrawing.For example, during transient operation, open electric heater 48 in the deflation maximum between wheel blade top and interior guard shield 40, so that projection 46 expansions, and make elongated element 32 withdrawals.In this embodiment, elongated element 32 has the CTE littler than the CTE of projection 46.
[0032], shown another embodiment of cover assembly 30 referring to Fig. 5.In this embodiment, elongated element 32 is arranged on the cylindrical bar of the hollow in the pipe 44.Pipe 44 extends through turbine cylinder 12, and by covering 56 outside seals with respect to turbine cylinder.In one embodiment, pipe 44 partly extends through the inside of the wall of turbine cylinder, and is therefore sealed by wall itself.Elongated element 32 is attached on the middle guard shield 38, and by positioning means 58 fix in position.Elongated element 32 can be connected on the positioning means 58 by mechanical attachment part (for example threaded attachment part or pin attachment), and perhaps elongated element 32 can only serve as centering machine, and charges in the pipe 44, moves around the axis of pipe 44 to prevent elongated element.Heating or cooling source can be applied to enter the mouth 50, to regulate the temperature of elongated element 32.
[0033] in an example, elongated element 32 has nine inches radial height, and turbine cylinder has six inches radial height, and outer shield has three inches radial height.
[0034] referring to Fig. 6, another embodiment of cover assembly 30 comprise extend through projection 46 and turbine cylinder 12 and be attached in the middle of elongated element 32 on the guard shield 38.Elongated element 32 is attached on fixing or the controlling mechanism 52.Shown in this embodiment, middle guard shield 38 forms " U " shape, should " U " shape can be designed to so that limit the retractible distance of elongated element.Except regulating temperature and providing the selected material with selected CTE, this feature also provides another kind of mechanism, with moving of guard shield 40 in controlling by this mechanism.In one embodiment, cover assembly comprises purging (purging) system 60.This purge system comprises the purging pipeline, to allow that cooling air or other material are applied to middle guard shield 38 and interior guard shield 40.
[0035] referring to Fig. 7, another embodiment of cover assembly 30 comprises the elongated element pipeline 64 of the part of the length that extends through elongated element 32.This partly hollow elongated element 32 on the outside that is positioned at turbine cylinder 12 of elongated element 32 or near end place comprise solid section.In this embodiment, can will be from the gas application of turbine cylinder inside and/or other thermal source in the inside of elongated element 32 by inlet 50, the outer end of elongated element 32 prevents that thermal source from escaping into the outside of turbine cylinder 12.
[0036] in another embodiment of cover assembly 30, outer shield 34 is opened the cave, and comprises pin 66 or make outer shield 34 be attached to other retention mechanism on the turbine cylinder 12.Pin 66 can remove in the axial direction, allowing axially to remove outer shield 34 again, thus can be near such as interior guard shield 40 members such as grade.Comprised that other pin or other retention mechanism are attached on the elongated element 32 middle guard shield 38.
[0037] referring to Fig. 8, another embodiment of cover assembly 30 comprises the elongated element 32 of hollow, and the elongated element 32 of this hollow has the pipeline 64 that extends along the whole length of elongated element 32.In this embodiment, the inside that can will be applied to elongated element 32 from discharge gas, cooling air, gas or steam or other material of turbo machine 10 from the outside of turbine cylinder 12.In one embodiment, include stable the use projection 68 outstanding towards the inside of elongated element pipeline, for example one or more independent projections or ring are to assist the elongated elements 32 in the stable pipe 44.
[0038] in another embodiment, fixing or controlling mechanism comprises the lock feature 70 that is attached on the alignment feature 71, it allows elongated element mechanically or in manual mode to align in pipe 44, with and/or allow elongated element 32 radially to advance or withdraw, to regulate the gap between interior guard shield 40 and the wheel blade top.In another embodiment, elongated element 32 is solid elongated elements.
[0039] referring to Fig. 9, another embodiment of cover assembly 30 comprises that locking/alignment covers 70, constructs and be attached to stable another embodiment with projection 68 on the turbine cylinder 12 individually, and sells 66.Provide other pin 72, so that middle guard shield 38 is fixed on the elongated element 32, and allows axially to remove pin 72, so that guard shield 38 in the middle of removing.In one embodiment, provide guard shield pipeline 74 to enter pipe 44 and leave from the inside of turbine cylinder 12 or from the gas in other source allowing by middle guard shield 38.
[0040] Figure 10-12 provide comprise be used to cool off in the structure of the cover assembly 30 used of the cooling of guard shield 40.In each of these structures, cover assembly comprise form in the middle of ring a plurality of guard shields 38 and a plurality of in guard shield 40.
[0041] Figure 10 has illustrated to comprise the structure of the elongated element 32 of hollow, by the elongated element 32 of this hollow, and guard shield 40 in can guiding to such as cooling sources 78 such as air, gas or steam.In this embodiment, the elongated element 32 of single hollow is associated with guard shield 38 in the middle of each. Guard shield 38 and 100 interior guard shields 40 in the middle of cover assembly 30 for example comprises 20.
[0042] referring to Figure 11, another embodiment of cover assembly 30 comprises the elongated element 32 of two hollows for guard shield 38 in the middle of each, and also comprises cavity 80 in middle guard shield 38, by this cavity 80, and guard shield 40 in cooling source 78 can being guided to.In this embodiment, cooling source 78 can enter and leave by the elongated element 32 of hollow, and also can enter by cavity 80. Guard shield 38 and 100 interior guard shields 40 in the middle of cover assembly 30 for example comprises ten.
[0043] in one embodiment, if having two or more elongated elements 32 for each cover assembly 30, then elongated element 32 extends parallel to each other.Each elongated element 32 equals zero with the mean of the angular deviation of the radial line of spinning axis extension.This orientation helps the combination that prevents that run duration from may occur.For example, if the 3rd elongated element 32 is placed on half place between preceding two elongated elements 32, the 3rd elongated element 32 line orientation radially then, and all these elongated elements 32 are parallel to each other.
[0044] Figure 12 has shown another embodiment of cooling scheme, comprises single elongated element for guard shield 38 in the middle of each, and comprises single cavity 80 for guard shield 38 in the middle of each.In another embodiment, for guard shield 38 in the middle of each, comprise any amount of elongated element and/or cavity 80.
[0045], provides a kind of system 90 that is used to control the gap between guard shield 34,38,40 and the one or more wheel blades top referring to Figure 13.This system can be combined in computer 91 and maybe can receive from user or other processing unit from the data of the sensor that combines with cover assembly.Displacement transducer 92 also is connected on the computer 91, thus computer 91 may command cover assemblies 30, to realize or to keep the gap of expectation.In one embodiment, cover assembly comprises or may be operably coupled to heating machanism, for example electric heater 48 and/or relay or be connected to other switch on the electric power source.In one embodiment, computer 91 is also connected to and can controls the thermal energy source, for example electric heater 48 and gas, steam and/or air source.Can utilize cover assembly 30 to comprise processing unit, perhaps the part as remote processing unit comprises processing unit.
[0046] in one embodiment, system 90 comprises computer 91, and this computer 91 is connected to such as on displacement transducer 92 devices such as grade, to measure the gap between wheel blade top and the cover assembly 30.Exemplary elements comprises (and unrestricted) at least one processor, storage, internal memory, input device, output unit etc.Because these members are known to those skilled in the art, so this paper does not carry out depicted in greater detail to these members.
[0047] in one embodiment, computer 91 is configured to so that guard shield 40 is withdrawn into original position in automatically making during the fault in detecting cover assembly 30.
[0048] substantially, some in the instruction of this paper are reduced to the instruction that is stored on the machine-readable medium.The output of expectation is carried out and is provided for the operator in this instruction by computer 91.
[0049] Figure 14 has illustrated to be used for regulating the illustrative methods 100 in the gap of the gas turbine that comprises turbine rotor and a plurality of wheel blades.Method 100 comprises one or more step 101-104.In one exemplary embodiment, this method comprises by described order and carries out all step 101-104.But, can omit some step, can add step, perhaps can change the order of step.In exemplary embodiment as herein described, be described in conjunction with cover assembly 30 and 91 pairs of these methods of computer.But, can come manner of execution 100 in conjunction with the processor of any kind, mode manner of execution 100 that perhaps can be manual.
[0050] in first step 101, cover assembly 30 is arranged on the turbine cylinder 12.Make elongated element 32 extend through at least a portion of the wall of turbine cylinder 12, and interior guard shield is positioned in the inside of turbine cylinder 12.
[0051] in second step 102, at first elongated element 32 is arranged to the radial distance selected apart from the inside of turbine cylinder 12.In one embodiment, this realizes by the radial distance that cover assembly 30 and appointment outer shield 34, middle guard shield 38 and/or interior guard shield 40 are set, thereby sets selected minimum range.In one embodiment, this can realize by making elongated element 32 radially move through pipe 44.In one embodiment, tighten (closest approach between wheel blade top and the interior guard shield 40 just) based on the maximum between wheel blade top and the interior guard shield 40 and select this minimum range.
[0052] in the 3rd step 103, starts turbo machine 10.Start and make turbine rotor and wheel blade 39 rotations again.
[0053] in the 4th step 104, will be applied to cover assembly 30 such as thermals source such as electric heater 46, steam, air so that interior guard shield 40 move and change in gap between in guard shield 40 and a plurality of wheel blades top at least one.In one embodiment, thermal source is applied to elongated element 32, so that the rising of the temperature of elongated element, thereby elongated element is expanded, and guard shield 40 advances towards the inside of turbine cylinder 12 in making, with the gap between guard shield 40 in reducing and the wheel blade top.In another embodiment, thermal source is applied to elongated element 32, reducing its temperature, so that interior guard shield 40 withdrawals and away from the inside of turbine cylinder 12.
[0054] in one embodiment, start electric heater 46, so that the temperature of projection 46 and/or elongated element 32 raises.In response, elongated element expands, and radially extends, with the gap between guard shield in reducing and the wheel blade top.In one embodiment, thermal source is by projection 46 and/or enter the mouth and 50 be applied to elongated element, so that interior guard shield 40 extends or withdrawal.As mentioned above, guard shield 40 extends with the temperature of rising elongated element and in making in the application of heat source, and uses cooling source and will reduce the temperature of elongated element and guard shield 40 is withdrawn.
[0055] in one embodiment, for example elongated element is remained on the chosen temperature by the air of using via pipeline 50 from the inside of turbine cylinder 12, thereby and, make elongated element 32 withdrawals by heat being applied to projection 46 and projection 46 being expanded and withdrawal elongated element 32.For example, during transient operation, open electric heater 48 in the deflation maximum between wheel blade top and interior guard shield 40, so that projection 46 expansions, and make elongated element 32 withdrawals.
[0056] though system and method as herein described provides in conjunction with gas turbine, can use the turbo machine of any other suitable type.For example, system and method as herein described can or comprise that gas takes place and the turbo machine of steam generation uses with steam turbine.
[0057] system and method as herein described provides the many advantages that are better than prior art system.For example, this system and method provides following technique effect: promptly allow ACTIVE CONTROL is carried out in the gap between wheel blade top and the guard shield, this ACTIVE CONTROL will allow the user with than prior art system gap operating turbine engines more closely.These system and methods are that guard shield is moved independently with the simple and low means of cost of control gap and solution manufacturing variation.
[0058] system and method as herein described allows than prior art system gap more closely, and this design with respect to prior art has improved whole efficiency.Prior art system adopts the guard shield of the independent segmentation that is kept together by the turbine casing hook.The gap is driven by the thermal time constant between turbine cylinder and the rotor/wheel blade simply.Wheel blade top/guard shield gap can be set enough highly, to prevent friction, still can not can not control this gap on one's own initiative under equilibrium condition under transient condition.System and method as herein described is favourable, because they provide the ACTIVE CONTROL to cover assembly during transient state and equilibrium condition.
[0059] can in software, firmware, hardware or their some combinations, implement embodiment's disclosed herein performance.As an example, one or more aspects of the disclosed embodiments can be included in the manufacturing article (for example one or more computer program) with medium that computer for example can use.Medium has comprised the computer-readable program code means that for example is used to provide and help performance of the present invention therein.Make the part that article can be included as computer system, perhaps can sell separately.In addition, can provide machine-readable, visibly comprise and to carry out at least a program storage device by machine with at least a instruction repertorie of the performance that realizes the disclosed embodiments.
[0060] substantially, this written description use-case comes open the present invention, comprises optimal mode, and also makes those skilled in the art can put into practice the present invention, comprises the method for making and using any device or system and implement any combination.But the scope of granted patent of the present invention is defined by the claims, and can comprise other example that those skilled in the art expect.If other such example has the structural element of the literal language that is tantamount to claims, if perhaps they comprise that literal language with claims does not have the equivalent structure element of essential distinction, other then such example intention is within the scope of exemplary embodiment of the present invention.
Claims (10)
1. system (10) that is used for regulating the gap of the gas turbine comprise turbine rotor (16) and a plurality of wheel blade (39), described system (10) comprising:
Comprise the cover assembly (30) of at least one sheath section (31), described at least one sheath section (31) is arranged in the inside of turbine cylinder (12); And
Elongated element (32) from described turbine cylinder (12) extension;
Wherein, described at least one sheath section (31) is attached on the end of described elongated element (32), described elongated element (32) is configured to so that move in response to temperature variation, so that described sheath section (31) moves and changes gap between in described sheath section (31) and the described a plurality of wheel blade (39) at least one.
2. system according to claim 1 (10) is characterized in that, the thermal expansion coefficient (CTE) of described elongated element (32) is different with the CTE of described turbine cylinder (12).
3. system according to claim 1 (10) is characterized in that, described system (10) further comprises the pipe (44) of at least a portion that extends through described turbine cylinder (12), and described elongated element (32) extends through described pipe (44).
4. system according to claim 3 (10) is characterized in that, the thermal expansion coefficient (CTE) of described elongated element (32) is different with the CTE of described pipe (44).
5. system according to claim 1 (10), it is characterized in that, described system (10) further comprises on the outside that is attached to described turbine cylinder (12) and is attached to projection (46) on the described elongated element (32), and be used for changing described projection (46) and described elongated element (32) at least one temperature, with the electric heat source of described projection (46) thermal communication.
6. system according to claim 1 (10), it is characterized in that described system (10) further comprises at least one the inlet (50) that passes through described elongated element (32) and described turbine cylinder (12) that is used for thermal source is guided to described elongated element (32).
7. system according to claim 1 (10) is characterized in that, described cover assembly (30) comprise be configured in case form the ring a plurality of sheath section (31).
8. an adjusting comprises the method (100) in the gap in the gas turbine of turbine rotor (16) and a plurality of wheel blade (39), and described method (100) comprising:
Cover assembly (30) is arranged on the turbine cylinder (12), and described cover assembly (30) comprises the sheath section (31) on the end that is attached to elongated element (32);
Described elongated element (32) is extended from described turbine cylinder (12), and described sheath section (31) is arranged in the inside of turbine cylinder (12); And
Thermal source is applied to described cover assembly (30),, and changes gap between in described sheath section (31) and the described a plurality of wheel blade (39) at least one so that described sheath section (31) moves.
9. method according to claim 8 is characterized in that, described cover assembly (30) comprises on the outside that is attached to described turbine cylinder (12) and is attached to projection (46) on the described elongated element (32).
10. method according to claim 9, it is characterized in that, use described thermal source and comprise described thermal source is applied to described projection (46), so that described projection (46) thermal expansion, and make described elongated element (32) radially move away from the described inside of described turbine cylinder (12).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/201174 | 2008-08-29 | ||
| US12/201,174 US20100054911A1 (en) | 2008-08-29 | 2008-08-29 | System and method for adjusting clearance in a gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101660431A true CN101660431A (en) | 2010-03-03 |
Family
ID=41606399
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910172097A Pending CN101660431A (en) | 2008-08-29 | 2009-08-28 | System and method for adjusting clearance in a gas turbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20100054911A1 (en) |
| JP (1) | JP2010053862A (en) |
| CN (1) | CN101660431A (en) |
| DE (1) | DE102009043832A1 (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102997811A (en) * | 2012-12-14 | 2013-03-27 | 贵州永红航空机械有限责任公司 | Radial clearance uniformity location and measuring device of turbine |
| CN103511003A (en) * | 2012-06-28 | 2014-01-15 | 中航商用航空发动机有限责任公司 | Control system |
| CN103717845A (en) * | 2011-08-02 | 2014-04-09 | 西门子公司 | A turbine system comprising a push rod arrangement between two housings |
| CN103925012A (en) * | 2013-01-10 | 2014-07-16 | 阿尔斯通技术有限公司 | Turbomachine with active electrical clearance control |
| CN105587342A (en) * | 2014-10-22 | 2016-05-18 | A.S.En.安萨尔多开发能源有限责任公司 | Turbine rotor blade with movable tail |
| CN106030048A (en) * | 2014-02-24 | 2016-10-12 | 西门子公司 | Heatable push rod for a steam turbine |
| CN106164417A (en) * | 2014-02-25 | 2016-11-23 | 西门子股份公司 | For the method by active hydraulic lash regulation operation gas turbine |
| CN106574778A (en) * | 2014-08-18 | 2017-04-19 | 川崎重工业株式会社 | Fuel injection device |
| CN109209515A (en) * | 2017-06-30 | 2019-01-15 | 安萨尔多能源英国知识产权有限公司 | For the guide vane carrier of gas turbine device and the gas turbine device including the guide vane carrier |
| CN112253264A (en) * | 2020-12-21 | 2021-01-22 | 中国航发上海商用航空发动机制造有限责任公司 | Device and method for regulating rotor-stator clearance and concentricity state |
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| US8593296B2 (en) * | 2010-10-19 | 2013-11-26 | General Electric Company | System and method for turbine bucket tip shroud deflection measurement |
| CH705551A1 (en) * | 2011-09-19 | 2013-03-28 | Alstom Technology Ltd | The self-adjusting device for controlling the clearance, especially in the radial direction between rotating and stationary components of a thermally loaded turbomachinery. |
| DE102013210876B4 (en) * | 2013-06-11 | 2015-02-26 | MTU Aero Engines AG | Composite component for thermal clearance control in a turbomachine and this turbomachine containing |
| JP6132786B2 (en) * | 2014-02-27 | 2017-05-24 | 三菱日立パワーシステムズ株式会社 | Clearance adjustment device, turbine device |
| US10760444B2 (en) | 2018-05-14 | 2020-09-01 | Raytheon Technologies Corporation | Electric heating for turbomachinery clearance control powered by hybrid energy storage system |
| US11111809B2 (en) * | 2018-05-14 | 2021-09-07 | Raytheon Technologies Corporation | Electric heating for turbomachinery clearance control |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103717845A (en) * | 2011-08-02 | 2014-04-09 | 西门子公司 | A turbine system comprising a push rod arrangement between two housings |
| CN103717845B (en) * | 2011-08-02 | 2016-02-17 | 西门子公司 | Turbine system and comprise the power generation system of this turbine system |
| CN103511003A (en) * | 2012-06-28 | 2014-01-15 | 中航商用航空发动机有限责任公司 | Control system |
| CN103511003B (en) * | 2012-06-28 | 2015-12-16 | 中航商用航空发动机有限责任公司 | Control system |
| CN102997811A (en) * | 2012-12-14 | 2013-03-27 | 贵州永红航空机械有限责任公司 | Radial clearance uniformity location and measuring device of turbine |
| CN102997811B (en) * | 2012-12-14 | 2015-08-26 | 贵州永红航空机械有限责任公司 | Turbine radial clearance uniformity location and measurement mechanism |
| CN103925012A (en) * | 2013-01-10 | 2014-07-16 | 阿尔斯通技术有限公司 | Turbomachine with active electrical clearance control |
| CN106030048A (en) * | 2014-02-24 | 2016-10-12 | 西门子公司 | Heatable push rod for a steam turbine |
| CN106030048B (en) * | 2014-02-24 | 2018-09-07 | 西门子公司 | Heatable push rod for steam turbine |
| CN106164417A (en) * | 2014-02-25 | 2016-11-23 | 西门子股份公司 | For the method by active hydraulic lash regulation operation gas turbine |
| CN106164417B (en) * | 2014-02-25 | 2018-10-19 | 西门子股份公司 | Method for adjusting operation gas turbine by active hydraulic lash |
| US10450967B2 (en) | 2014-02-25 | 2019-10-22 | Siemens Aktiengesellschaft | Method for the operation of a gas turbine by active hydraulic gap adjustment |
| CN106574778A (en) * | 2014-08-18 | 2017-04-19 | 川崎重工业株式会社 | Fuel injection device |
| CN105587342A (en) * | 2014-10-22 | 2016-05-18 | A.S.En.安萨尔多开发能源有限责任公司 | Turbine rotor blade with movable tail |
| CN105587342B (en) * | 2014-10-22 | 2019-04-02 | A.S.En.安萨尔多开发能源有限责任公司 | Turbine rotor blade with moveable end |
| CN109209515A (en) * | 2017-06-30 | 2019-01-15 | 安萨尔多能源英国知识产权有限公司 | For the guide vane carrier of gas turbine device and the gas turbine device including the guide vane carrier |
| CN112253264A (en) * | 2020-12-21 | 2021-01-22 | 中国航发上海商用航空发动机制造有限责任公司 | Device and method for regulating rotor-stator clearance and concentricity state |
| CN112253264B (en) * | 2020-12-21 | 2021-04-02 | 中国航发上海商用航空发动机制造有限责任公司 | Device and method for regulating rotor-stator clearance and concentricity state |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2010053862A (en) | 2010-03-11 |
| DE102009043832A1 (en) | 2010-03-04 |
| US20100054911A1 (en) | 2010-03-04 |
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Application publication date: 20100303 |