CN105402028B - Rib plate eddy flow control structure, rotation disk cavity system and gas turbine - Google Patents
Rib plate eddy flow control structure, rotation disk cavity system and gas turbine Download PDFInfo
- Publication number
- CN105402028B CN105402028B CN201510214714.7A CN201510214714A CN105402028B CN 105402028 B CN105402028 B CN 105402028B CN 201510214714 A CN201510214714 A CN 201510214714A CN 105402028 B CN105402028 B CN 105402028B
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- rib
- floor
- control vortex
- floor control
- turbine disk
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a rib plate eddy flow control structure arranged in a rotation disk cavity. The rib plate eddy flow control structure comprises: a rib plate, wherein the rib plate presents a ring; and a plurality of same first ribs arranged on the rib plate first surface facing the disk surface of the rotation wheel disk and projecting toward the disk surface, wherein the plurality of the first ribs are circumferentially and uniformly arranged on the rib plate at intervals, and limit the first gas flow guiding path between the first surface of the rib plate and the disk surface.
Description
Technical field
The present invention relates to the floor control in gas turbine and aero-engine technology field, more particularly to a kind of inside rotating disc cavities
Vortex structure, the inside rotating disc cavities system with the floor control vortex structure.
Background technology
In gas turbine and aero-engine air system, it is very that gas outwardly or inwardly flows through inside rotating disc cavities
Common fluidal texture, has each different functions in diverse location, the flowing of the inside rotating disc cavities with different structure.Than
Such as：Inside rotating disc cavities positioned at generator terminal of calming the anger are generally used for bleed, and this strand of gas enters inside rotating disc cavities via compressor rotor root
Inwardly it flow to up to core, then through different streams, reaches gas turbine diverse location, realizes high-temperature component cooling, bearing bore
The various functions such as obturage；Draw air into turbine disk chamber from compressor, in disk chamber outwardly, by the turbine disk of low radius
The heart to high radius disk edge flows to cool down the turbine disk, finally turns stator root from turbine and enter sprue to turn stator root to obturage
Portion, prevents main flow 1000～2200K high-temperature fuel gas from pouring in down a chimney into turbine disk chamber；Turbo blade prewhirl gas handling system by increase into
Enter the tangential velocity of the inside rotating disc cavities internal gas flow that cover plate is constituted with the turbine disk, reduce the relative stagnation temperature of cooling gas, reach more
The effect of the good cooling turbine disk with turbo blade.
Found according to substantial amounts of theoretical and experimental study：During gas is via inside rotating disc cavities outwardly or inwardly flow process, by
In the intrinsic Wesco pump effect of rotation roulette, the fluid near rotation card has very big tangential velocity, and this can cause whirlpool
The generation of stream, causes the very big pressure loss, so for the control of disk chamber flowing is at all the control to being vortexed.
However, for the disk chamber of difference in functionality, because the target to be realized is different, the control strategy taken is not needed also not
It is identical.
For generator terminal bleed disk chamber of calming the anger, it is desirable to bleed disk intracavity gas are reduced as far as possible along journey flow losses, with less
Bleed air pressure, bleed temperature, amount of air entrainment complete to obturage with cooling to lift gas turbine overall efficiency, extend making for hot-end component
Use the life-span.For this purpose, for the inside rotating disc cavities that this radial direction becomes a mandarin, the control strategy taken is needed to be to reduce disk chamber to enter
Mouth speed ratio, the development for suppressing circumferential eddy currents, reduce the pitot loss caused due to strong circumferential eddy currents.
For turbine turns-quiet system's disk chamber (the disk chamber being made up of rotation roulette and stator part), strengthen the cooling effect of the turbine disk
Really, reduce and turn cooling tolerance needed for stator root is obturaged and reduce because the main flow aerodynamic loss that gas blending of obturaging is caused is
The target of disk chamber flow optimized.The taken strategy of optimization is the internal flow of adjustment plate chamber：For enhanced heat exchange, by increase
The tangential velocity of cooling air, reduces air-flow with respect to stagnation temperature；For reducing mixing loss, the fluid tangent line speed of adjustment plate chamber outlet
Spend the tangential velocity of the main flow combustion gas close to turning, at the position of stator boundary.
Turbo blade is prewhirled and turn-transfer from one department to another the disk chamber (disk being made up of the rotor element of two same rotational speeds in system
Chamber), the tangential velocity of adjustment plate chamber internal gas flow so that the air-flow tangential velocity of turbine blade cooling channel entrance and this radius
The card tangential velocity at place is identical, inlet flow loss is reduced, so as to improve blade cooling channel entrance pressure, it is ensured that blade is cold
Tolerance reaches requirement.The control strategy taken be make the gas in fin passage to force whirlpool in the way of move, it is ensured that air-flow
Tangential velocity is equal with local card tangential velocity all the time.
The content of the invention
The present invention proposes a kind of simple, general control inside rotating disc cavities internal vortex and produces and the structure for developing.The knot
Structure can be used in the centripetal or centrifugal flow of disk intracavity；Can be used for turning-quiet system's disk chamber, turn-transfer from one department to another disk chamber.By control panel chamber
Internal vortex develops, and realizes different targets, such as：Bleed pitot loss, adjustment axial force are reduced, strengthened heat exchange, reduced main flow
With Secondary Flow mixing loss etc..
In general, the present invention for the technical scheme that adopted of its technical problem of solution for：Propose that one kind is applied in rotation
The floor control vortex structure of disk intracavity.
According to an embodiment of the invention on one side, it is proposed that a kind of floor control whirlpool knot being arranged in inside rotating disc cavities
Structure, including：Floor, the floor is annular in shape；With the multiple first ribs of identical, the card in the face of rotation roulette of floor is arranged in
First surface on and towards the card protrusion, the plurality of first rib evenly-spaced cloth in the circumferential direction of floor
Put, the plurality of first rib limits the first air-flow path of navigation between the first surface and the card of floor.
A kind of another aspect according to embodiments of the present invention, it is proposed that inside rotating disc cavities system, including：Centrifugal compressor disk
Chamber, centrifugal impeller disc portion limits the centrifugal compressor disk chamber；Turbine disk chamber, turbine disk segment limits the turbine disk chamber,
Wherein：Connected by seal structure between centrifugal compressor disk chamber and turbine disk chamber；In centrifugal compressor disk chamber and turbine disk chamber
At least one in be provided with floor control vortex structure, the floor control vortex structure includes：Floor, the floor is annular in shape；With it is identical
Multiple first ribs, be arranged in floor on the first surface of the card of rotation roulette and towards the card protrusion, institute
State multiple first ribs evenly-spaced arrangement in the circumferential direction of floor, the plurality of first rib floor first surface with
The first air-flow path of navigation is limited between the card.
Another further aspect according to embodiments of the present invention, it is proposed that a kind of inside rotating disc cavities system, including turbine disk chamber, the turbine disk
Part limits the turbine disk chamber, wherein：Turbine disk intracavity is provided with floor control vortex structure, and floor control vortex structure includes：Floor,
The floor is annular in shape；With the multiple first ribs of identical, be arranged in floor on the first surface of the card of rotation roulette
And towards card protrusion, the plurality of first rib evenly-spaced arrangement in the circumferential direction of floor, the plurality of the
One rib limits the first air-flow path of navigation between the first surface and the card of floor, and the floor control vortex structure is applied to
Turbine blade cooling is prewhirled in system, and the floor is fixed on the wheel disk of turbine as rotation roulette, floor and wheel disk of turbine
Card between form turbine disk chamber, multiple first holes that turbine disk chamber is flowed into for air-flow are provided with the floor, per a pair
At least one first holes are provided with circumference between adjacent first rib.
A kind of further aspect according to embodiments of the present invention, it is proposed that gas turbine, including above-mentioned inside rotating disc cavities system.
Description of the drawings
The basic feature of the present invention will by specific embodiment, with reference to accompanying drawing carry out deeper into explanation.In detail below
Embodiment is a part of embodiment of the present invention, does not constitute inappropriate limitation of the present invention.
Fig. 1 be according to one exemplary embodiment of the present invention, floor control vortex structure applied in centrifugal compressor disk chamber
And the sectional view in turbine disk chamber, larger arrow specifies main flow flow direction in figure, and smaller directional arrow specifies air system
Flow path direction.
Fig. 2 is the rib in the centrifugal compressor disk chamber being applied in Fig. 1 according to one exemplary embodiment of the present invention
The structural representation of plate；
Fig. 3 is the schematic perspective view of the floor in Fig. 2；
Fig. 4 is to be applied in centrifugal compressor disk according to another exemplary embodiment, the floor control vortex structure of the present invention
Sectional view in chamber and turbine disk chamber；
Fig. 5 is knot exemplary embodiment, applying floor in the centrifugal compressor disk chamber of Fig. 4 according to the present invention
Structure schematic diagram；
Fig. 6 be according to the present invention it is exemplary embodiment, be applied to centripetal flow disk chamber to strengthen the floor of eddy flow
Structural representation；
Fig. 7 is the knot of the floor in the turbine disk chamber being applied in Fig. 1 according to one exemplary embodiment of the present invention
Structure schematic diagram；
Fig. 8 be according to one exemplary embodiment of the present invention, apply the rib prewhirled in turbine blade cooling in system
The sectional view of plate control vortex structure；
Fig. 9 is the structural representation of floor in Fig. 8.
Specific embodiment
Below by embodiment, and accompanying drawing is combined, technical scheme is described in further detail.Following ginsengs
It is intended to explain the present general inventive concept of the present invention according to explanation of the accompanying drawing to embodiment of the present invention, and is not construed as
The a kind of of the present invention is limited.
As shown in figure 1, the present invention is applied to bleed air stream and turbine disk cooling flowing path, centrifugal compressor disk chamber
4 are made up of centrifugal impeller disk 1, floor 2, stator casing 3, ring 7 of obturaging；Turbine disk chamber 5 is by the turbine disk 9, floor 6 (including rib row
11 with rib arrange 12), ring 7 of obturaging constitutes.
Centrifugal impeller and the turbine disk are rotated counterclockwise (see from left to right) around rotary shaft 8, and smaller directional arrow represents air in Fig. 1
System path direction：The air of compressor sprue enters disk chamber 4 through Centrifugal Impeller Rotor root slit, into disk chamber 4
Gas first passes around the inward flow of floor 2, flows into big chamber at low radius；The gas in big chamber is flowed into through seal structure for example
Comb tooth 10 enters turbine disk chamber 5, into the cooling air in turbine disk chamber 5 through the surface of floor 6 and the turbine disk 9 to outflow
It is dynamic, turn stator root into sprue and main flow combustion gas mixing through turbine.
As shown in figure 1, floor control vortex structure is applied to rotor-stator cavity chamber centripetal flow structure including：Constitute the centrifugation in disk chamber
Compressor disk, the floor with multi-form rib, the stator casing for constituting disk chamber, the centrifugal impeller disk 1 and stator casing
Form air system tap air channel.
As shown in figure 1, floor 2 can be fixed on stator casing by way of welding or mode connects for screw.
It is applied to the disk chamber control strategy that inwardly flows typically to take " subtracting rotation "：It is to reduce pitot loss to subtract rotation purpose.It is few
Take in the case of number " increasing rotation ", it is therefore intended that increase radial direction differential static pressure, reduce card axial load, adjustment rotor axial power is only
In thrust bearing working range.
Floor is provided with circumferential equally distributed rib on the face of centrifugal impeller side, rib can for different shape, no
With deviation angle.The deviation angle of rib refers to the centrage of rib and the angle of compressor disk radial direction.The deflection angle of rib on floor
Between 0 degree～90 degree, the angle with come flow absolute air flow angle it is identical when, rib passage entrance loss is minimum.Arrange have with
Can reduce to flow the loss into rib-rib passage to flow absolute air flow angle identical rib, while the passage energy between rib and rib
The development of circumferential eddy currents is enough controlled, by the rib for designing different structure, the speed ratio for the making air-flow to design (tangential velocity of air-flow
With the ratio of the tangential velocity of local card) Changing Pattern inwardly flows along rib-rib passage.When speed ratio reduces, eddy flow
Weaken, realize " subtracting rotation "；When speed ratio increases, eddy flow is strengthened, and realizes " increasing rotation ".For be installed at low radius for subtracting
The rib structure of few pitot loss, adjustment rib-rib passage outlet absolute air flow angle is 0 degree, can eliminate the rotation of channel outlet air-flow
Turn the impact of the negotiability for downstream flow passage component.
Floor can be arranged at the high radius in disk chamber or low radius according to different control targes.When needing, reduction is total along Cheng
When crushing loses or increases disk chamber axial load, floor can be installed at the high radius in disk chamber, directly reduce the rotation of inlet air flow
Turn ratio, it is also possible to be installed at low radius, have the effect for becoming apparent to suppressing free vortex；When need reduce card axial load
When, floor is installed at the high radius in disk chamber, airflow inlet speed ratio is increased by floor, strengthen the development of eddy flow, Jin Erzeng
Platter surface radial direction differential static pressure, reduces card average pressure, final to reduce card axial load.
Rib is circumferentially uniformly distributed on floor, and fin quantity is determined according to the radial position of fin place, it is ensured that fin row's tool
There is certain denseness.The final goal that the length of rib can be distributed adjustment according to vortex control with disk cavity pressure considers to carry out
Select.Floor can arrange its structure in the disk intracavity of related application with cantilever pattern arrangement, solve structure heat under temperature field action
The problem of Stress Release.
The height of rib is determined by floor with the spacing of rotation roulette card, it is ensured that the top of rib is more than with rotation roulette spacing
Such as 1.0mm, it is preferable that for 1.5mm is avoiding touching mill.But, the spacing is also unsuitable excessive, to avoid the gas of more share
The non-modulated passage just passed through between floor and rotation roulette of stream, for example, the spacing can be less than 5mm.The height of rib is needed
Guarantee has enough effective flow areas.
The shape of rib can be straight rib, curved ribs, guide vane form.According to the different purposes of " increasing rotation " from " subtracting rotation ",
Carry out different designs.
The concrete structure of floor 2 is as shown in Figure 2 and Figure 3.Air into disk chamber 4 is in the slit that wheel disc 1 and floor 2 are formed
Flow radially inward, different rib-rib passages can control circumferential eddy currents during air inward flow on floor
Development.
Floor 2 can as shown in Figure 1 loaded at high radius, it is also possible to as shown in Figure 4 loaded on low radius at.Loaded on low radius
The floor at place is exported closer to for reduction flow rotation ratio has more direct and obvious effect due to range hadn wheel chamber.
The height of rib determines according to card curve form on floor 2 shown in Fig. 4 so that rib top is with card apart from basic one
Cause, it is ensured that gas as much as possible is in rib-rib passage.
The α of floor entrance angle shown in Fig. 2 is equal to moving air import absolute air flow angle radially inward, and ω show centrifugation
Impeller direction of rotation.Fig. 2 show simple straight rib structure, and rib import rounding reduces rib-rib passage entrance loss.Rib row also may be used
To be designed as guide vane form according to Fig. 5, Fig. 6, the rib-rib passage outlet flow angle of form floor shown in Fig. 5 is essentially 0
Degree, for weakening eddy flow；The channel outlet flow angle of version floor shown in Fig. 6 is β, and β is more than entrance angle α, for increasing
Strong eddy flow.
Research shows that stream air can cause downstream passage component discharge coefficient to reduce when having larger circumferential speed, such as schemes
Centrifugal pan chamber exit comb tooth 10 in 1, and this impact is particularly evident to orifice plate.So, version floor shown in Fig. 5 is used for
At low radius, the pressure loss can not only be reduced, while exit flow circumferential speed can be eliminated affecting on downstream components.
Floor 6 is used in turbine disk chamber 5 in Fig. 1, installs and original big turbine disk chamber is changed into into shallow bid chamber after floor, can
Reduction turbine disk chamber turns the flow of obturaging needed for stator root, while completely cutting off radiant heat transfer of the guider internal ring to the turbine disk.
Being arranged at the main target of the floor control vortex structure in turbine disk intracavity portion is：Enhanced heat exchange, strengthens cooling gas pair
The cooling effect of the turbine disk；Reduce and cool down the aerodynamic loss caused to main flow when gas is released into main flow from end wall of obturaging.For increasing
Strong cooling gas are arranged at the low radius in disk chamber to the rib of turbine disk cooling effect.Blend for reducing obturage gas and main flow of cooling
The rib of loss is generally positioned at the high radius in disk chamber, by adjustment plate chamber exit flow angle so that leak into main flow from end wall
Gas with close to the tangential velocity of rotor main flow import import main flow combustion gas, reduce mixing loss.Specifically, such as Fig. 1 institutes
Show have the rib row 11 being located at respectively at low radius to arrange 12 with the rib at high radius on floor 6.Rib row 11 at low radius is controlled
Strategy processed is：Adjustment cooling air-flow angle so that air-flow tangential velocity increases, so as to reduce the relative stagnation temperature of air-flow, enhanced heat exchange,
Compared with traditional preswirl nozzle, the flow field that rib structure is obtained is more uniform, eliminates card localized heat stress concentration；Positioned at height
Rib at radius arranges 12 control strategies：Rib row 12 is disposed in proximity to turn stator root, the turbine disk of main flow will will be imported
Cooling air tangential velocity is adjusted to close to the tangential velocity of main flow combustion gas herein, reduces blending for the pneumatic damage that main flow is caused
Lose.
Fig. 7 is that the rib at low radius arranges 11 concrete structure schematic diagrams.Air-flow enters rib and arranges passage with very low tangential velocity,
Air-flow tangential velocity is greatly increased after rib is arranged, and so as to reduce the relative stagnation temperature of air-flow, strengthens the heat exchange of the turbine disk.
In FIG, big disk chamber is divided into into loculus by installing long floor 6, can reduces and turn stator root and obturage institute
Air demand, so as to reduce air system amount of air entrainment.
Application of the rib in centripetal flow disk chamber is analogous to, the deflection angle and import in the turbine disk chamber middle rib of centrifugal flow
Flow angle is equal, rib import carries out rounding, rib and certain denseness is circumferentially uniformly distributed and kept on floor.
What floor control vortex structure applied also for that turbo blade prewhirls that system cover plate and the turbine disk formed turn-leaves heart stream
Moving plate chamber.Turn from turbine-quiet system's disk chamber is different, floor be used for be herein in order to control blade path inlet air flow tangential velocity with
Local card is identical, reduces the blade path inlet air flow pressure loss, improves the pressure of the air for blade cooling, it is ensured that leaf
Piece cooling tolerance is sufficient.Fig. 8 show another embodiment of the floor in the system of disk chamber, and this embodiment is applied to rib structure
Turbine blade cooling is prewhirled in system.Arrow represents cooling air flow direction, and from the stream of pre- trepanning 4 cooling air point in chamber 5 is entered
For three strands, one flows into chamber 13 and turns stator root to obturage through comb tooth 12, prevents main flow high-temperature fuel gas from pouring in down a chimney；One stock-traders' know-how
Cross comb tooth 11 and exit into another chamber；One enters turbine disk chamber 6 through receiver hole 9.Into the cooling gas in turbine disk chamber 6
Body radially flows, and access aperture 10 is to cooling turbine bucket after floor 2.Floor 2 is fixed on rotation roulette 3,
Pivot together with wheel disc 3.Appropriate design rib arranges shape so that before access aperture 10, disk at gas tangential velocity and this radius
Face tangential velocity is identical, reduces entrance loss.Simultaneously floor 2 rotates and the cooling air work done in rib-rib passage can be increased
Blade air conditioning quantity, it is ensured that blade long-term work under high temperature and high load lotus state.The concrete structure of floor 2 is as shown in figure 9, using straight rib
Row, it is ensured that air-flow speed ratio in rib-rib passage is always 1 (ratio of air-flow tangential velocity and local card tangential velocity).
To sum up, the present invention proposes following scheme：
1st, a kind of floor control vortex structure being arranged in inside rotating disc cavities, including：
Floor, the floor is annular in shape；With
The multiple first ribs of identical, be arranged in floor on the first surface of the card of rotation roulette and towards described
Card is protruded, the plurality of first rib evenly-spaced arrangement in the circumferential direction of floor, and the plurality of first rib is in floor
First surface and the card between limit the first air-flow path of navigation.
2nd, according to 1 floor control vortex structure, wherein：The air flow inlet end of first rib is rounded.
3rd, according to 1 floor control vortex structure, wherein：Spacing between the top of first rib and the card of rotation roulette exists
1.0mm-5.0mm between.
4th, according to 1 floor control vortex structure, wherein：The floor is arranged on stator casing.
5th, according to 4 floor control vortex structure, wherein：The import deflection angle of each first rib is substantially equal to flow definitely
Flow angle, the import deflection angle of first rib refers to the centrage of the inducer of first rib and the angle of rotation roulette radial direction.
6th, according to 4 or 5 floor control vortex structure, wherein：The inside rotating disc cavities be centrifugal compressor disk chamber, the rotating wheel
Disk is centrifugal impeller disk.
7th, according to 6 floor control vortex structure, wherein：The first rib is arranged near the radial inner end of wheel disc card.
8th, according to 7 floor control vortex structure, wherein：The first rib is curved ribs, and the outlet deflection angle of first rib is big
Cause as 0 degree, the outlet deflection angle of first rib refers to the centrage of the outlet section of first rib and the angle of rotation roulette radial direction.
9th, according to 7 floor control vortex structure, wherein：One end of floor is fixed to and extends to propping up for centrifugal compressor disk intracavity
Frame, the support is fixed on stator casing.
10th, according to 6 floor control vortex structure, wherein：The first rib is arranged near the radial outer end of wheel disc card.
11st, according to 5 or 10 floor control vortex structure, wherein：The first rib is curved ribs, and the outlet deviation of first rib
Angle is more than the import deflection angle, and the outlet deflection angle of first rib refers to the centrage of the outlet section of first rib and rotation roulette footpath
To angle.
12nd, according to 10 floor control vortex structure, wherein：The first rib is straight rib.
13rd, according to 10 floor control vortex structure, wherein：Stator of the one end of floor near Centrifugal Impeller Rotor root
On casing.
14th, according to 5 floor control vortex structure, wherein：The rotation roulette is the turbine disk, and the floor is from centrifugal compressor
The seal structure in disk chamber extends about the turbine disk and turns near stator root, between the floor and the turbine disk turbine to be formed
Disk chamber, the turbine disk chamber is communicated by the seal structure with the centrifugal compressor disk chamber.
15th, according to 14 floor control vortex structure, wherein：The plurality of rib also includes multiple second ribs of identical, is arranged in
Floor on the first surface of the card of rotation roulette and towards the card protrusion, the plurality of second rib is in floor
Evenly-spaced arrangement in circumferential direction, the plurality of second rib limits second between the first surface and the card of floor
Air-flow path of navigation；The plurality of first rib is arranged in the radial inner end of floor, and at least part of air-flow from seal structure enters
Enter the gas channel between multiple first ribs；The plurality of second rib is arranged in the radial outer end of floor and turns quiet near the turbine disk
Daughter root portion, gas channel between multiple second ribs of at least part of air-flow of turbine disk intracavity and enter combustion gas sprue.
16th, according to 15 floor control vortex structure, wherein：The first rib is curved ribs, and the outlet deflection angle of first rib
It is designed to increase the tangential velocity of the exit flow for flowing out the gas channel between first rib, the outlet deflection angle of first rib is referred to
The centrage of the outlet section of first rib and the angle of rotation roulette radial direction；Second rib is curved ribs, and the footpath of the second rib is outside
End turns stator wheel rim near the turbine disk, and the outlet deflection angle of the second rib is configured so as to flow out the gas channel between the second rib
Exit flow tangential velocity it is close with main flow combustion gas tangential velocity, the outlet deflection angle of the second rib refers to the outlet of the second rib
The centrage of section and the angle of rotation roulette radial direction.
17th, according to 15 floor control vortex structure, wherein：The air flow inlet end of the second rib is rounded.
18th, according to 14 floor control vortex structure, wherein：First rib is provided only with the floor, one end of first rib is leaned on
The radial inner end of nearly floor, the other end turns stator root near the turbine disk.
19th, according to 4 floor control vortex structure, wherein：One end of floor is fixed to stator casing, and the other end is free end.
20th, according to 1 floor control vortex structure, wherein：The floor control vortex structure is applied to turbine blade cooling prewhirls and is
In system, the floor is fixed on the wheel disk of turbine as rotation roulette, and between floor and the card of wheel disk of turbine turbine is formed
Disk chamber, is provided with multiple first holes that turbine disk chamber is flowed into for air-flow on the floor, the circumferential adjacent first rib per a pair
Between be provided with least one first holes.
21st, according to 20 floor control vortex structure, wherein：The first rib is straight rib, and the outlet deflection angle of first rib is substantially
For 0 degree, the outlet deflection angle of first rib refers to the centrage of first rib and the angle of wheel disk of turbine radial direction.
22nd, according to 21 floor control vortex structure, wherein：One the is provided between circumferential adjacent first rib per a pair
One hole, all of first hole is equidistantly spaced from along a circumference, and the radial inner end of each first rib extended the first hole place
Circumference, the radial outer end of each first rib is near turbine blade cooling channel entrance.
23rd, a kind of inside rotating disc cavities system, including：Centrifugal compressor disk chamber, centrifugal impeller disc portion limits the centrifugation pressure
Mechanism of qi disk chamber；Turbine disk chamber, turbine disk segment limits the turbine disk chamber, wherein：Centrifugal compressor disk chamber and turbine disk chamber it
Between by seal structure connect；Be provided with interior with least one of turbine disk chamber of centrifugal compressor disk chamber is appointed according in 1-5,19
The floor control vortex structure of one.
24th, according to 23 inside rotating disc cavities system, wherein：Centrifugal compressor disk intracavity is provided with according in claim 6-13
Floor control vortex structure described in any one.
25th, according to 23 or 24 inside rotating disc cavities system, wherein：Turbine disk intracavity is provided with according in claim 14-18
Floor control vortex structure described in any one.
26th, a kind of inside rotating disc cavities system, including turbine disk chamber, turbine disk segment limits the turbine disk chamber, wherein：Turbine
Disk intracavity is provided with the floor control vortex structure according to any one of 20-22.
27th, a kind of gas turbine, including the inside rotating disc cavities system according to any one of 23-26.
The floor control vortex structure of the present invention is produced by installing the floor with rib in disk intracavity to the vortex of disk intracavity
One of regulated and controled with development, the invention at least has the advantage that：
1., simple structure, is highly susceptible to realizing.Simple rib structure, it is easy to processing and installation, it is lightweight, while by
Being installed on stator part (a few cases are also installed in rotor element) in floor can avoid vibration problem.
2., the form of rib is changeable on floor, and straight rib, curved ribs, guide vane form rib are designed as needed.
3., rib structure is widely used.The rib structure can apply to that disk chamber is centripetal or centrifugal flow.Can realize subtracting
Few disk chamber bleed pitot loss；Adjustment plate intracavity portion's pressure distribution is so as to adjusting the axial load that rotor thrust bearing is born；
Adjustment plate intracavity portion cooling air-flow angle, so as to reduce relative stagnation temperature, strengthens heat exchange；Adjustment plate chamber turns stator root leakage stream and cuts
Linear velocity is close to turbine rotor import main flow tangential velocity, reduces mixing loss.
4., floor can play heat-insulated effect.Being installed on the floor in centrifugation back of the body chamber can completely cut off the biography of combustor heat
Lead, being installed on the floor in turbine disk chamber can completely cut off combustor exit high temperature stator casing for the heat of the turbine disk conducts, and
And floor is thin-slab structure, one end is free end, can free wxpansion, the lower structure thermal stress of different temperatures distribution can be solved
Release problem.
Furthermore, it is necessary to explanation, the specific embodiment described in this specification, is named the shape of its parts and components
Title etc. can be with difference.The equivalent or simple change that all constructions according to described in inventional idea of the present invention, feature and principle are done, wraps
Include in the protection domain of patent of the present invention.Those skilled in the art can be embodied as to described
Example is made various modifications or supplements or substituted using similar mode, structure without departing from the present invention or surmounts this
Scope as defined in the claims, all should belong to protection scope of the present invention.
Claims (22)
1. a kind of floor control vortex structure being arranged in inside rotating disc cavities, including：
Floor, the floor is annular in shape；With
The multiple first ribs of identical, be arranged in floor on the first surface of the card of rotation roulette and towards the card
Protrusion, the plurality of first rib evenly-spaced arrangement in the circumferential direction of floor, the plurality of first rib in floor the
The first air-flow path of navigation is limited between one surface and the card；
The floor is arranged on stator casing.
2. floor control vortex structure according to claim 1, wherein：
The air flow inlet end of first rib is rounded.
3. floor control vortex structure according to claim 1, wherein：
Spacing between the top of first rib and the card of rotation roulette is between 1.0mm-5.0mm.
4. floor control vortex structure according to claim 1, wherein：
The import deflection angle of each first rib is substantially equal to flow absolute air flow angle, and the import deflection angle of first rib refers to
The centrage of the inducer of one rib and the angle of rotation roulette radial direction.
5. the floor control vortex structure according to claim 1 or 4, wherein：
The inside rotating disc cavities are centrifugal compressor disk chamber, and the rotation roulette is centrifugal impeller disk.
6. floor control vortex structure according to claim 5, wherein：
The first rib is arranged near the radial inner end of wheel disc card.
7. floor control vortex structure according to claim 6, wherein：
The first rib is curved ribs, and substantially 0 degree of the outlet deflection angle of first rib, and the outlet deflection angle of first rib refers to the
The centrage of the outlet section of one rib and the angle of rotation roulette radial direction.
8. floor control vortex structure according to claim 6, wherein：
One end of floor is fixed to the support for extending to centrifugal compressor disk intracavity, and the support is fixed on stator casing.
9. floor control vortex structure according to claim 5, wherein：
The first rib is arranged near the radial outer end of wheel disc card.
10. the floor control vortex structure according to claim 4 or 9, wherein：
The first rib is curved ribs, and the outlet deflection angle of first rib is more than the import deflection angle, and the outlet of first rib is inclined
Knuckle refers to the centrage of the outlet section of first rib and the angle of rotation roulette radial direction.
11. floor control vortex structures according to claim 9, wherein：
The first rib is straight rib.
12. floor control vortex structures according to claim 9, wherein：
One end of floor is on the stator casing near Centrifugal Impeller Rotor root.
13. floor control vortex structures according to claim 4, wherein：
The rotation roulette is the turbine disk, and the floor is extended about to the turbine disk from the seal structure in centrifugal compressor disk chamber and turned
Near stator root, turbine disk chamber is formed between the floor and the turbine disk, the turbine disk chamber passes through the knot of obturaging
Structure is communicated with the centrifugal compressor disk chamber.
14. floor control vortex structures according to claim 13, wherein：
The plurality of rib also includes multiple second ribs of identical, is arranged in the first surface of the card in the face of rotation roulette of floor
Above and towards card protrusion, the plurality of second rib evenly-spaced arrangement in the circumferential direction of floor is the plurality of
Second rib limits the second air-flow path of navigation between the first surface and the card of floor；
The plurality of first rib is arranged in the radial inner end of floor, and at least part of air-flow from seal structure enters multiple first
Gas channel between rib；
The plurality of second rib is arranged in the radial outer end of floor and turns stator root near the turbine disk, and turbine disk intracavity is at least
Gas channel of the fraction between multiple second ribs and enter combustion gas sprue.
15. floor control vortex structures according to claim 14, wherein：
The first rib is curved ribs, and the outlet deflection angle of first rib is designed to the gas channel that increase is flowed out between first rib
Exit flow tangential velocity, the outlet deflection angle of first rib refers to centrage and the rotation roulette footpath of the outlet section of first rib
To angle；
Second rib is curved ribs, and the radial outer end of the second rib turns stator wheel rim near the turbine disk, and the outlet of the second rib is inclined
Knuckle is configured so that the tangential velocity and main flow combustion gas tangential velocity of the exit flow for flowing out the gas channel between the second rib
Close, the outlet deflection angle of the second rib refers to the centrage of the outlet section of the second rib and the angle of rotation roulette radial direction.
16. floor control vortex structures according to claim 14, wherein：
The air flow inlet end of the second rib is rounded.
17. floor control vortex structures according to claim 13, wherein：
It is provided only with first rib on the floor, near the radial inner end of floor, the other end is near the turbine disk for one end of first rib
Turn stator root.
18. floor control vortex structures according to claim 1, wherein：
One end of floor is fixed to stator casing, and the other end is free end.
A kind of 19. inside rotating disc cavities systems, including：
Centrifugal compressor disk chamber, centrifugal impeller disc portion limits the centrifugal compressor disk chamber；
Turbine disk chamber, turbine disk segment limits the turbine disk chamber,
Wherein：
Connected by seal structure between centrifugal compressor disk chamber and turbine disk chamber；
Centrifugal compressor disk chamber is interior with least one of turbine disk chamber to be provided with according to claim 1-4, any one of 18 institutes
The floor control vortex structure stated.
20. inside rotating disc cavities systems according to claim 19, wherein：
Centrifugal compressor disk intracavity is provided with the floor control vortex structure according to any one of claim 5-12.
The 21. inside rotating disc cavities systems according to claim 19 or 20, wherein：
Turbine disk intracavity is provided with the floor control vortex structure according to any one of claim 13-17.
22. a kind of gas turbines, including the inside rotating disc cavities system according to any one of claim 19-21.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510214714.7A CN105402028B (en) | 2015-04-30 | 2015-04-30 | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine |
| CN201611258387.6A CN106677903B (en) | 2015-04-30 | 2015-04-30 | Floor control vortex structure, inside rotating disc cavities system, gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510214714.7A CN105402028B (en) | 2015-04-30 | 2015-04-30 | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611258387.6A Division CN106677903B (en) | 2015-04-30 | 2015-04-30 | Floor control vortex structure, inside rotating disc cavities system, gas turbine |
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| Publication Number | Publication Date |
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| CN105402028A CN105402028A (en) | 2016-03-16 |
| CN105402028B true CN105402028B (en) | 2017-05-03 |
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| CN201611258387.6A Active CN106677903B (en) | 2015-04-30 | 2015-04-30 | Floor control vortex structure, inside rotating disc cavities system, gas turbine |
| CN201510214714.7A Active CN105402028B (en) | 2015-04-30 | 2015-04-30 | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine |
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| CN201611258387.6A Active CN106677903B (en) | 2015-04-30 | 2015-04-30 | Floor control vortex structure, inside rotating disc cavities system, gas turbine |
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| CN105888850B (en) * | 2016-06-12 | 2018-05-25 | 贵州航空发动机研究所 | A kind of vane type preswirl nozzle with rectification rib |
| CN106640739B (en) * | 2016-12-24 | 2018-11-06 | 中国科学院工程热物理研究所 | A kind of adjustable centrifugal compressor circumferential weld bleed structure |
| CN107131009B (en) * | 2017-05-16 | 2019-02-15 | 中国科学院工程热物理研究所 | A kind of self-locking seal structure of turbomachine and the engine with it |
| CN107725479B (en) * | 2017-09-26 | 2019-09-24 | 中国科学院工程热物理研究所 | A kind of rotor casing structure inside inside rotating disc cavities and the engine comprising the structure |
| CN109555603B (en) * | 2017-09-27 | 2020-01-10 | 中国航发商用航空发动机有限责任公司 | Composite material sealing cover and preparation method thereof |
| CN110318874B (en) * | 2019-06-24 | 2020-09-25 | 中国科学院工程热物理研究所 | Vortex control path system of centrifugal compressor back cavity in gas turbine |
| CN110608815A (en) * | 2019-09-18 | 2019-12-24 | 西北工业大学 | Method for measuring relative total temperature of airflow in cavity of rotating disk |
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| CN113217120B (en) * | 2020-01-21 | 2023-08-08 | 中国航发商用航空发动机有限责任公司 | High-pressure turbine cooling air supply system and aeroengine |
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| CN112377308A (en) * | 2020-10-28 | 2021-02-19 | 北京航空航天大学 | Anti-rotation fin type vortex reduction system with high-radius outlet |
| CN112412544A (en) * | 2020-11-23 | 2021-02-26 | 东方电气集团东方汽轮机有限公司 | Gas turbine pneumatic hole type prerotation nozzle with inlet transition section |
| CN113123999B (en) * | 2021-03-26 | 2022-01-28 | 北京航空航天大学 | Shunting cooling type aero-engine compressor rear shaft diameter conical wall cavity |
| CN113123998A (en) * | 2021-03-26 | 2021-07-16 | 北京航空航天大学 | Compressor conical wall cavity for inhibiting vortex formation |
| CN112983648B (en) * | 2021-04-13 | 2022-04-01 | 浙江大学 | Gas turbine radial air inlet chamber flow active control device |
| CN113357189B (en) * | 2021-06-23 | 2022-11-18 | 中国航发湖南动力机械研究所 | Radial outflow impeller back cavity air-entraining structure and gas turbine engine |
| CN114151141B (en) * | 2021-10-20 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Aeroengine turbine disk cavity gas collection flow guide structure |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN106677903A (en) | 2017-05-17 |
| CN105402028A (en) | 2016-03-16 |
| CN106677903B (en) | 2018-07-20 |
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