CN103016153A - Axial force adjusting device for rotor of gas turbine - Google Patents
Axial force adjusting device for rotor of gas turbine Download PDFInfo
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- CN103016153A CN103016153A CN2013100079678A CN201310007967A CN103016153A CN 103016153 A CN103016153 A CN 103016153A CN 2013100079678 A CN2013100079678 A CN 2013100079678A CN 201310007967 A CN201310007967 A CN 201310007967A CN 103016153 A CN103016153 A CN 103016153A
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- gas turbine
- axial force
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- turbine rotor
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Abstract
The invention relates to an axial force adjusting device for a rotor of a gas turbine and belongs to the structural design for the gas turbine. The adjusting device comprises a gas compressor, a turbine and a rotating shaft, wherein a sealing ring is mounted behind a final-stage wheel disc of the turbine, and an unloading chamber is formed by the final-stage wheel disc of the turbine and the sealing ring through enclosing and tightly sealed by using a rotary static sealing device. The axial force of the rotor of the gas turbine can be effectively adjusted through adjusting the pressure of air in the unloading chamber. The axial force adjusting device for the rotor of the gas turbine has the advantages that the change of the axial force of the rotor of the gas turbine caused by the combustion of low-calorie fuels can be effectively reduced, the stability of the operation of the rotor of the gas turbine is improved, and the design cost for the gas turbine is reduced.
Description
Technical field
The present invention relates to the structural design of gas turbine, relate in particular to a kind of gas turbine rotor axial force controlling device, belong to the gas-turbine plant technical field.
Background technique
China's coal reserves is huge, and is very large to the dependence of coal fuel, but for traditional thermoelectricity generating, directly uses coal fuel and can bring various environmental pollution problem.Therefore the main development direction in China modern gas turbines power station is to make synthetic gas with coal, makes coal be converted into the energy of cleaning, adopts gas turbine power generation take synthetic gas as fuel again, reduces the pollution to environment.Therefore modern gas turbines requires not only can use traditional light oil, rock gas etc., and more requirement can be used the clean fuels such as producing synthesis gas from coal and hydrogen.
For saving cost and simplifying development process, the General Requirements gas turbine can be under the change condition of trying one's best few, realization uses the unit design of fuels with different heat values, and use fuels with different heat values instead, when particularly using synthetic gas fuel instead, because the calorific value of synthetic gas fuel is very low, the fuel quantity that consumes when reaching same combustor exit temperature increases, and causes the combustor exit flow to increase.Therefore with the gas turbine take high-energy fuel such as rock gases as basic design, when changing to the gas turbine of the low calorie fuelss such as synthetic gas, the gas flow of combustor exit and turbine import will increase, and comparatively general change method is for changing firing chamber and turbine one-level stator for this reason.This change method can make the variation of firing chamber adaptation fuel, increases simultaneously the throat area of turbine one-level stator.But change the subject matter that turbine one-level stator brings be, because the throat area of turbine one-level stator changes, gas flow also changes, and the outlet pressure that uses the gas turbine turbine one-level stator of high low calorie fuels will have very large difference.
The change of this pressure will cause the gas turbine rotor axial force to vary widely under the fuels with different heat values condition, thereby affect the operational reliability of gas turbine rotor.For fear of rotor axial power large variation occurs, traditional solution is when using fuels with different heat values, to come the Choice and design thrust bearing according to gas turbine maximum rotor axial force.Use the thrust bearing that the gas turbine of low calorie fuels selects than the gas turbine that uses higher calorific value large, therefore this scheme will increase the design difficulty of thrust bearing and also can increase the design cost of gas turbine.
Summary of the invention
The purpose of this invention is to provide a kind of gas turbine rotor axial force controlling device, so that the rotor axial power excursion of gas turbine is little when using fuels with different heat values, thereby the operational reliability of Effective Raise gas turbine rotor, the design cost of reduction gas turbine.
The technical solution adopted in the present invention is as follows:
A kind of gas turbine rotor axial force controlling device, this controlling device comprises gas compressor, turbine and rotating shaft, it is characterized in that: a seal ring is installed in the final stage wheel disc back at turbine, and final stage wheel disc and seal ring surround a unloading cavity, and obturage with turning static seal device.
In the technique scheme, described unloading cavity is connected with gas compressor by gas compressor bleed gas circuit.Preferably, be connected with pipeline between described unloading cavity and the gas compressor bleed gas circuit, and on pipeline or the front position of gas compressor bleed gas circuit throttling arrangement is housed.
Another technical characteristics of the present invention is: described unloading cavity is connected by pipeline with external air source, and throttling arrangement is housed on the pipeline.Described throttling arrangement is orifice structure or modulating valve.Described external air source is the outside pressure-increasing machine of setting up or the exhaust heat boiler in the Combined Cycle Unit.
The static seal device that turns of the present invention adopts castor tooth, honeycomb, brush or graphite seal structure.
The present invention compared with prior art has the following advantages and the high-lighting effect: gas turbine rotor axial force controlling device of the present invention reaches the purpose of adjusting the gas turbine rotor axial force by the air pressure in the control unloading cavity.Compared with prior art, not only can effectively reduce because the variation of the gas turbine rotor axial force that lower heat of combustion fuel produces improves the stability of gas turbine rotor operation; Also avoid simultaneously because rotor axial power increases the thrust bearing that needs employing large, thus the design difficulty of reduction thrust bearing and reduce the design cost of gas turbine.
Description of drawings
Fig. 1 is the overall structure schematic diagram of gas turbine rotor axial force controlling device.
Fig. 2 is gas turbine rotor axial force controlling device the first embodiment's structural principle schematic diagram.
Fig. 3 is gas turbine rotor axial force controlling device the second embodiment's structural principle schematic diagram.
Fig. 4 is the third embodiment's of gas turbine rotor axial force controlling device structural principle schematic diagram.
Symbol description is as follows among the figure:
The 1-gas compressor; 2-gas compressor bleed gas circuit; The 3-pipeline; The 4-throttling arrangement; The 5-unloading cavity; The 6-turbine; The 7-rotating shaft; 8-final stage wheel disc; 9-turns static seal device; The 10-seal ring; The 11-pressure-increasing machine; The 12-motor.
Embodiment
Below in conjunction with accompanying drawing principle of the present invention, structure and embodiment are described further.
Fig. 1 is the overall structure schematic diagram of gas turbine rotor axial force controlling device, this controlling device comprises gas compressor 1, turbine 6 and rotating shaft 7, a seal ring 10 is installed in final stage wheel disc 8 back at turbine 6, final stage wheel disc 8 surrounds a unloading cavity 5 with seal ring 10, and obturages with turning static seal device 9.The described static seal device 9 that turns can adopt castor tooth, honeycomb, brush or graphite seal structure.
Unloading cavity 5 is that the final stage wheel disc 8 by turbine 6 surrounds a chamber with seal ring 10, and obturages with the air that turn in 9 pairs of unloading cavities of static seal device 5, thereby guarantees the pressure that unloading cavity 5 is interior.
Fig. 2 is gas turbine rotor axial force controlling device the first embodiment's structural principle schematic diagram.This gas turbine rotor axial force controlling device can directly be joined gas compressor 1 and unloading cavity 5 by gas compressor bleed gas circuit 2, selects to regulate air pressure in the unloading cavity 5 from gas compressor 1 bleed not at the same level.
When using low calorie fuels, the fuel quantity that consumes when reaching same combustor exit temperature increases, cause the combustor exit flow to increase, the outlet pressure of gas turbine turbine one-level stator will increase, thereby causes gas turbine rotor axial force generation increment backward.Because gas compressor gas pressure differences corresponding to stator that turn at different levels, the gas pressure of low pressure stage is lower than the gas pressure of high pressure stage, as shown in dotted line among Fig. 2, gas compressor bleed gas circuit from which grade bleed of gas compressor can be adjusted as required, thereby so that the gas pressure of drawing from gas compressor satisfies pressure required in the unloading cavity, to reach the purpose of effective regulating gas turbine wheel axial force.
Fig. 3 is gas turbine rotor axial force controlling device the second embodiment's structural principle schematic diagram.This controlling device comprises gas compressor 1, gas compressor bleed gas circuit 2, turbine 6 and rotating shaft 7, in final stage wheel disc 8 back of turbine 6 seal ring 10 is installed, and final stage wheel disc 8 surrounds 10 1 unloading cavities 5 with seal ring, and obturages with turning static seal device 9; Be connected with pipeline 3 between unloading cavity 5 and the gas compressor bleed gas circuit 2, throttling arrangement 4 is housed on the pipeline.Described throttling arrangement can adopt orifice structure or modulating valve.
Utilize pipeline that the air in the gas compressor is guided in the unloading cavity by gas compressor bleed gas circuit.Throttling arrangement adopts orifice structure, reaches the purpose of regulating unloading cavity internal pressure size by using different orifice plates instead.Thereby because increasing, the air quantity in the unloading cavity produces an axial force forward, this axial force can offset because the rotor axial power part that lower heat of combustion fuel causes axial force to increase, thereby so that the gas turbine rotor axial force can not produce very large variation because of lower heat of combustion fuel, guarantee the gas turbine rotor reliability of operation.
Fig. 4 is the third embodiment's of gas turbine rotor axial force controlling device structural principle schematic diagram.This controlling device comprises gas compressor 1, turbine 6 and rotating shaft 7, in final stage wheel disc 8 back of turbine 6 seal ring 10 is installed, and final stage wheel disc 8 surrounds a unloading cavity 5 with seal ring 10, and obturages with turning static seal device 9; Unloading cavity 5 is connected with external air source by pipeline 3, and throttling arrangement 4 is housed on the pipeline 3; External air source can adopt pressure-increasing machine 11 that the outside sets up or the exhaust heat boiler in the Combined Cycle Unit.
Utilize pipeline from the external air source bleed in unloading cavity, reach the purpose of regulating unloading cavity inner air pressure size by the throttling arrangement of regulating on the pipeline.This embodiment is regulating gas turbine wheel axial force effectively also.
Claims (7)
1. gas turbine rotor axial force controlling device, this controlling device comprises gas compressor (1), turbine (6) and rotating shaft (7), it is characterized in that: a seal ring (10) is installed in final stage wheel disc (8) back at turbine (6), final stage wheel disc (8) surrounds a unloading cavity (5) with seal ring (10), and obturages with turning static seal device (9).
2. a kind of gas turbine rotor axial force controlling device as claimed in claim 1 is characterized in that: described unloading cavity (5) is connected with gas compressor (1) by gas compressor bleed gas circuit (2).
3. a kind of gas turbine rotor axial force controlling device as claimed in claim 2, it is characterized in that: be connected with pipeline (3) between described unloading cavity (5) and the gas compressor bleed gas circuit (2), and on pipeline or the front position of gas compressor bleed gas circuit throttling arrangement (4) is housed.
4. a kind of gas turbine rotor axial force controlling device as claimed in claim 1, it is characterized in that: described unloading cavity (5) is connected by pipeline with external air source, and throttling arrangement is housed on the pipeline.
5. such as claim 3 or 4 described a kind of gas turbine rotor axial force controlling devices, it is characterized in that: described throttling arrangement is orifice structure or modulating valve.
6. a kind of gas turbine rotor axial force controlling device as claimed in claim 1 is characterized in that: described static seal device (9) employing castor tooth, honeycomb, the brush or graphite seal structure of turning.
7. a kind of gas turbine rotor axial force controlling device as claimed in claim 4 is characterized in that: described external air source is the outside pressure-increasing machine of setting up or the exhaust heat boiler in the Combined Cycle Unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013100079678A CN103016153A (en) | 2013-01-09 | 2013-01-09 | Axial force adjusting device for rotor of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013100079678A CN103016153A (en) | 2013-01-09 | 2013-01-09 | Axial force adjusting device for rotor of gas turbine |
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| Publication Number | Publication Date |
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| CN103016153A true CN103016153A (en) | 2013-04-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2013100079678A Pending CN103016153A (en) | 2013-01-09 | 2013-01-09 | Axial force adjusting device for rotor of gas turbine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104727950A (en) * | 2015-02-10 | 2015-06-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial force control device for combustion gas turbine and control method thereof |
| CN106014649A (en) * | 2016-07-13 | 2016-10-12 | 上海电气燃气轮机有限公司 | Axial force adjusting system for gas turbine |
| CN113358260A (en) * | 2021-06-25 | 2021-09-07 | 北京化工大学 | Test bed for testing axial pneumatic thrust of rotating-static disc cavity |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1034607A (en) * | 1987-01-28 | 1989-08-09 | 通用电气公司 | Tractor steam piston balancing |
| CN101994524A (en) * | 2009-08-03 | 2011-03-30 | 通用电气公司 | System and method for modifying rotor thrust |
| RU2420668C1 (en) * | 2009-11-24 | 2011-06-10 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Double-flow gas turbine engine |
| CN203130259U (en) * | 2013-01-09 | 2013-08-14 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial force adjusting device of gas turbine rotor |
-
2013
- 2013-01-09 CN CN2013100079678A patent/CN103016153A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1034607A (en) * | 1987-01-28 | 1989-08-09 | 通用电气公司 | Tractor steam piston balancing |
| CN101994524A (en) * | 2009-08-03 | 2011-03-30 | 通用电气公司 | System and method for modifying rotor thrust |
| RU2420668C1 (en) * | 2009-11-24 | 2011-06-10 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Double-flow gas turbine engine |
| CN203130259U (en) * | 2013-01-09 | 2013-08-14 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial force adjusting device of gas turbine rotor |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104727950A (en) * | 2015-02-10 | 2015-06-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial force control device for combustion gas turbine and control method thereof |
| CN104727950B (en) * | 2015-02-10 | 2019-10-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine axial direction force control device and its control method |
| CN106014649A (en) * | 2016-07-13 | 2016-10-12 | 上海电气燃气轮机有限公司 | Axial force adjusting system for gas turbine |
| CN106014649B (en) * | 2016-07-13 | 2018-04-17 | 上海电气燃气轮机有限公司 | Gas turbine axial direction draught control system |
| CN113358260A (en) * | 2021-06-25 | 2021-09-07 | 北京化工大学 | Test bed for testing axial pneumatic thrust of rotating-static disc cavity |
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Application publication date: 20130403 |