CN1497129A - Turbine transmission mechanism and method for cooling turbine transmission mechanism - Google Patents
Turbine transmission mechanism and method for cooling turbine transmission mechanism Download PDFInfo
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- CN1497129A CN1497129A CNA2003101024626A CN200310102462A CN1497129A CN 1497129 A CN1497129 A CN 1497129A CN A2003101024626 A CNA2003101024626 A CN A2003101024626A CN 200310102462 A CN200310102462 A CN 200310102462A CN 1497129 A CN1497129 A CN 1497129A
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Abstract
The invention relates to a turbine engine with a turbine shalt which has a number of disks arranged adjacent to one another, to each of which a number of moving blades are fastened in a star arrangement, wherein these moving blades can be cooled with at least one coolant which flows through coolant channels inside the moving blades. The object of this invention is to increase the efficiency at an economically justifiable cost and at the same time to lower the operating risk and to increase the service life of the elements and the reliability of the turbine engine. To this end, coolant is supplied to and discharged from the moving blades via a simple and reliable coolant feeder system which is structured in a radial multilayered fashion between two adjacent disks.
Description
Technical field
The present invention relates to a kind of turbine driving mechanism that has a turbine spindle, the wheel disc that has a plurality of settings adjacent one another are on this turbine spindle, but on these wheel discs respectively radial fixing moving vane, wherein these moving vanes can be cooled off by at least a cooling medium that flows through the inner coolant guiding channel of moving vane.
The invention still further relates to the method for this turbine driving mechanism of cooling.
Background technique
In a lot of fields the turbine driving mechanism is housed all, it mainly is used as the transmission device in the aviation industry and is used for produce power.In energy-producing situation, distinguish combustion gas turbine and steam turbine, this two classes machinery is used to drive generator, is called so-called combustion gas-steam turbine device (GuD-Anlagen) when usually using at the same time.In the combustion gas turbine of Kao Lving fuel-AIR MIXTURES is imported the firing chamber below, the working medium that forms in the firing chamber flows out from the firing chamber, flows through these moving vanes and expansion working along the moving vane direction.By means of moving vane the transformation of energy of working medium is become kinetic energy, by the rotation of turbine spindle described kinetic energy is passed to generator again.
Usually fuel air mixture burns under 1200 ℃ to 1300 ℃ temperature conditions radiationlessly, can obtain high efficiency whereby.Usually can efficient further be improved by further raising combustion temperature.
Be at working medium under the situation of combustion temperatures, thermostability, mechanical strength and life-span of the parts of the turbine driving mechanism that contacts with working medium proposed peak demand.Therefore, should be issued to high as far as possible efficient in the condition of considering each parts operation risk and Economy.
Moving vane for the turbine driving mechanism also requires it to have thermostability, long life and high reliability.In order to make the moving vane that is seen as first order moving vane group from the working medium flow direction can bear maximum heat load, moving vane is cooled off with known manner.For this reason, allow usually become cooling but the cavity of the bypass passage system of media flow pass these moving vanes.Adopt pressurized air or steam or adopt both simultaneously as cooling medium.Certainly, the cooling performance of steam is better than the compression air.But steam is higher to the sealing requirements of whole cooling system, this means that the manufacturing expense that is used for the delivery cooling medium is higher.
As everyone knows, moving vane is by air and/or steam cooling.Air cooling can be used as open or closed cooling and realizes, and steam cooling only is applicable to enclosed cooling system.When the moving vane to the turbine driving mechanism cooled off, it was very high desiring to keep pressure reduction very big between working medium and cooling medium expense technically.For described zone is isolated from each other, require on whole cooling medium delivery approach, to set up the sealing system of a high cost, so that leakage loss is very little, thereby guarantee effective cooling.Shortcoming is exigent for this reason economy and technical costs, in addition, and owing to technical sophistication has reduced safety in operation and reliability.
Because the structure that adopts single parts to pack into, be very difficult to each moving vanes of different moving vane groups with the cooling medium delivery, and also need very high expense to guarantee desired system sealing and operational reliability.
Summary of the invention
The technical problem to be solved in the present invention is: improve the efficient of turbine driving mechanism under the prerequisite of reasonable financial cost, reduce operating risk simultaneously, promptly improve the life-span of parts and the reliability of turbine driving mechanism.
According to the present invention, the technological scheme that addresses the above problem is: in the turbine driving mechanism that this specification begins partly to mention, between two wheel discs that are closely adjacent to each other, radially surround and form a plurality of cavitys of along the circumferential direction encircling (umgreifen) turbine spindle respectively, and cooling medium has different pressure in these cavitys, and wherein one or more cooling mediums can flow into these cavitys respectively and can flow out from these cavitys.
At this, starting point of the present invention is: the simplification to moving vane delivery cooling medium can reduce operating risk.Can advantageously reduce the number of Sealing thus when shortening the seal length that is kept, this has improved safety in operation, has reduced rate of fault, and has reduced the leakage loss of cooling medium.In addition, also can adopt the simple seal system of same reduction operating risk.In this case, flow in the cooling medium that can make multiple different performance each cavity between two adjacent wheel discs, as fresh air and/or delivery " fresh " cooling medium to the fresh steam of moving vane, and/or " being used " cooling medium as the used steam that used air and/or passive blade dispatch are come out.This better way provides the measure of cooling medium to allow to use effectively cooling medium, and helps raising the efficiency, and can bear higher temperature because be exposed to the member of working medium.
Especially preferred structure of the present invention is arranged like this: by centrifugal seal spare the cavity of radially adjoining is sealed each other.The sealing means in this very reliable radially adjoining zone has reduced the leakage loss of cooling medium.
The all-in-one-piece cooling channel communicates with the same cavity that this wheel disc and an adjacent wheel disc encirclement form by a radial bore or path in one of moving vane on the same wheel disc if all are arranged on, and then advantageously obtains a kind of reliable connection of sealing fully.
Preferably one of described at least cavity communicates with a cooling medium supplying mouth or cooling medium exhaust port.
Cool off the method for above-mentioned turbine driving mechanism according to the present invention, the pressure that flows through the cooling medium of a cavity is higher than the pressure of the cooling medium of the next-door neighbour's cavity that flows through radial outward.Therefore, under the rough sledding that very firm basically centrifugal seal damages, the leakage loss of appearance only leaks into that less one-level of pressure of next-door neighbour from a pressure level, that is to say the cavity that only leaks into the next-door neighbour of radial outward from a cavity.
In the method for a kind of cooling turbine driving mechanism of the present invention, flow in the described radially innermost cavity is fresh steam, flow into the described steam that was to use that radially is close in its outer cavity, flowing in the cavity of described radially outermost is fresh air.Combustion gas turbine usually has the steam turbine operation (combustion gas-steam turbine device) of the steam of different pressures as working medium with multistage needs.From the working medium steam of high-pressure steam turbine, extract the parts that a part is used to cool off combustion gas turbine.In this application, that part of steam of extraction is called fresh steam, and its number pressure magnitude is about 40 crust (bar).The used steam that has returned after having cooled off the parts that bear hot combustion gas, be about 30 crust (bar) can be used as the working medium delivery to a medium pressure steam turbine.Therefore, can advantageously repeatedly use cooling medium steam.The fresh steam that occurs at failure condition leaks part because pressure only reduces towards the flow direction of used steam takes place, and with used vapor mixing.Used steam is admitted to the medium pressure steam turbine again, thereby has reduced the loss that caused by leakage.Because the direction that leakage reduces along pressure flows and mixes with fresh air, then this part steam can continue on for cooling as the used steam of fruit part.During blow-by, cooling medium loss partly appears just only between the flow channel of zone that fresh air flows and combustion gas turbine working medium.
Therefore, the invention describes a kind of radially multilayer system that forms by the zone that has different pressures and be isolated from each other, at this moment, radially from inside to outside have a pressure to fall.See that radially prevailing in the penetralia cavity between adjacent wheel disc is the maximum pressure that is produced by fresh steam, prevailing in radial outward next-door neighbour's the cavity is the inferior low-pressure that is produced by used steam, prevailing in the radially outside again most external cavity is the lower pressure that is produced by fresh air, and prevailing in the flow channel between turbine spindle and rotor is the minimum pressure that is produced by working medium.Its advantage is: shortened seal length that along the circumferential direction moves towards between the described wheel disc and the different pressures cooling medium layered arrangement for further partly utilizing leak fluid to adopt suitably when reducing number of seals.
Description of drawings
Exemplarily the present invention is elaborated below in conjunction with accompanying drawing.
Fig. 1 illustrates to have described the partial view of the combustion gas turbine that has turbine spindle not in scale.
Embodiment
Fig. 1 shows the section of the combustion gas turbine 17 that dissects along the rotating shaft 2 of turbine spindle 1.On turbine spindle 1, be provided with wheel disc 3,4 and 5 adjacent to each other.Be fixed with the moving vane 14 of forming moving vane group 16 in first, second and the 3rd turbine stage on these wheel discs 3,4 and 5 respectively.Each turbine stage is arranged on guide vane group on the stator 18 and one by one and keeps close watch over the moving vane group 16 that is connected on guide vane group downstream along working medium A flow direction and constitute.Guide vane 15 also is located at outside not shown gas supply assembly by one and supplies with fresh air, and this represents with flow arrow 10.
The wheel disc 3,4 and 5 cavitys 8,9 and 20 that ring-type is encircled turbine spindle that are arranged on adjacent to each other on the turbine spindle 1 are enclosed between them.Inner cavity 8 is positioned at inner radial, and is relative with middle cavity 9.External cavity 20 is radially locating to encircle middle cavity 9 outwardly.Make inner cavity 8 with respect to middle cavity 9 sealings by means of a centrifugal seal spare 6, same, middle cavity seals with respect to cavity 20 by a centrifugal seal spare.Not shown, the groove (Fase) that is placed on two adjacent wheel discs by the centrifugal seal spare that constitutes of sealing wire rod is gone up with its reliable location.Boring or path 7 that inner cavity 8 has an one coolant guiding channel supplying mouth that is used to make this cavity 8 and moving vane 14 to communicate.Thereby inner cavity 8 is used for providing cooling medium to moving vane 14.Equally, cavity 9 also has a boring 7 that communicates with the moving vane 14 one coolant guiding channel outflow openings that are used to flow out cooling medium.
Mobility status by means of 22 pairs of cooling mediums of second turbine stage describes below.Fresh steam axially flows to the inner cavity 8 that constitutes between wheel disc 3 and 4 along turbine spindle 1 from the cooling medium source, represent with fresh steam flow arrow 12.The supplying mouth of hole 7 delivery that described fresh steam flows through in the wheel disc 4 trend radially again moving vane 4 in second turbine stage 22.Fresh steam plays cooling action in this moving vane 14, and flows out through exhaust port.Be arranged on used steam delivery that another radial hole 7 at exhaust port place will represent with flow arrow 13 to the middle cavity 9 that surrounds by wheel disc 4 and 5.Used steam flows out from cavity 9 and flows into another cavity 23 by an axial passage, therefrom used steam is seen off again.
Flowing through behind the guide vane 15 delivery to again from the fresh air 10 of a unshowned fresh air sources is positioned at radially than cavity 9 cavity 20 more outwardly.Fresh air from these cavity 20 delivery to moving vane 14.Then, the fresh air of discharging at moving vane 14 back ribs mixes with the working medium A of combustion gas turbine.
By configuration of the present invention, promptly between wheel disc 3,4 and 5, radially form cavity 8,9,20 coaxially separatedly by a distance and simply and reliably seal these cavitys with centrifugal seal spare, can realize a kind of favourable device.In conjunction with method of the present invention, promptly supply with the cooling medium of different performance, different pressures (from inside to outside successively decreasing) to cavity 8,9,20, compared with prior art can be significantly improved.
Claims (6)
1. turbine driving mechanism that has turbine spindle, the wheel disc that has a plurality of settings adjacent one another are on this turbine spindle, but on these wheel discs respectively radial fixing moving vane, wherein these moving vanes can be cooled off by at least a cooling medium that flows through the inner coolant guiding channel of moving vane, it is characterized in that: between two wheel discs that are closely adjacent to each other, radially surround and form a plurality of cavitys of along the circumferential direction encircling described turbine spindle respectively, and cooling medium has different pressure in these cavitys, wherein said one or more cooling mediums can flow into these cavitys respectively, and can flow out from these cavitys.
2. turbine driving mechanism as claimed in claim 1 is characterized in that: described cavity radially adjacent one another are seals each other.
3. turbine driving mechanism as claimed in claim 1 or 2 is characterized in that: all are arranged on, and the all-in-one-piece cooling channel communicates with the same cavity that this wheel disc and an adjacent wheel disc encirclement form by a radial bore or path in one of moving vane on the same wheel disc.
4. as each described turbine driving mechanism in the claim 1 to 3, it is characterized in that: one of described at least cavity communicates with a cooling medium supplying mouth or cooling medium exhaust port.
5. method that is used for cooling off as claim 1 to 4 turbine driving mechanism as described in each, it is characterized in that: the pressure that flows through the cooling medium of a cavity is higher than the pressure of the cooling medium of the next-door neighbour's cavity that flows through radial outward.
6. the method for a moving vane of cooling turbine driving mechanism as claimed in claim 5, it is characterized in that: flowing in the described radially innermost cavity is fresh steam, flow into the described steam that was to use that radially is close in its outer cavity, flowing in the cavity of described radially outermost is fresh air.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2003101024626A CN1497129A (en) | 2002-10-21 | 2003-10-21 | Turbine transmission mechanism and method for cooling turbine transmission mechanism |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP02023472.0 | 2002-10-21 | ||
| CNA2003101024626A CN1497129A (en) | 2002-10-21 | 2003-10-21 | Turbine transmission mechanism and method for cooling turbine transmission mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN1497129A true CN1497129A (en) | 2004-05-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2003101024626A Pending CN1497129A (en) | 2002-10-21 | 2003-10-21 | Turbine transmission mechanism and method for cooling turbine transmission mechanism |
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| CN (1) | CN1497129A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102146810A (en) * | 2010-02-10 | 2011-08-10 | 中国科学院工程热物理研究所 | Method for cooling high-temperature turbine blade by utilizing supercritical characteristics of working medium |
| CN102369358A (en) * | 2009-05-14 | 2012-03-07 | Mtu飞机发动机有限公司 | Flow device comprising a cavity cooling system |
| CN103790709A (en) * | 2014-02-19 | 2014-05-14 | 中国航空动力机械研究所 | Turbine disk |
| CN106523035A (en) * | 2015-09-11 | 2017-03-22 | 熵零股份有限公司 | Hydraulic shaft gas impeller mechanism, hydraulic shaft gas turbine and device comprising hydraulic shaft gas turbine |
-
2003
- 2003-10-21 CN CNA2003101024626A patent/CN1497129A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102369358A (en) * | 2009-05-14 | 2012-03-07 | Mtu飞机发动机有限公司 | Flow device comprising a cavity cooling system |
| CN102146810A (en) * | 2010-02-10 | 2011-08-10 | 中国科学院工程热物理研究所 | Method for cooling high-temperature turbine blade by utilizing supercritical characteristics of working medium |
| CN103790709A (en) * | 2014-02-19 | 2014-05-14 | 中国航空动力机械研究所 | Turbine disk |
| CN103790709B (en) * | 2014-02-19 | 2017-07-28 | 中国航空动力机械研究所 | Wheel disk of turbine |
| CN106523035A (en) * | 2015-09-11 | 2017-03-22 | 熵零股份有限公司 | Hydraulic shaft gas impeller mechanism, hydraulic shaft gas turbine and device comprising hydraulic shaft gas turbine |
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