CN105402028A - 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
- CN105402028A CN105402028A CN201510214714.7A CN201510214714A CN105402028A CN 105402028 A CN105402028 A CN 105402028A CN 201510214714 A CN201510214714 A CN 201510214714A CN 105402028 A CN105402028 A CN 105402028A
- Authority
- CN
- China
- Prior art keywords
- rib
- floor
- chamber
- turbine disk
- control vortex
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
Landscapes
- 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 gas turbine and aero engine technology field, particularly relate to the floor control vortex structure in a kind of inside rotating disc cavities, there is the inside rotating disc cavities system of this floor control vortex structure.
Background technique
In gas turbine and aeroengine air system, gas, through the inside rotating disc cavities inwardly or outwardly right and wrong fluidal texture of usually seeing, is in diverse location, has the flowing of the inside rotating disc cavities of different structure and have functions different separately.Such as: the inside rotating disc cavities being positioned at gas compressor end is generally used for bleed, this strand of gas enters inside rotating disc cavities via compressor rotor root and inwardly to flow arrival core, pass through different stream again, arrive gas turbine diverse location, realize the various functions such as high-temperature component cools, bearing bore is obturaged; Turbine disk chamber is entered from air that gas compressor draws, in dish chamber outwardly, flowed with cooling turbine dish to high radius dish edge by the turbine core of low radius, finally turn stator root from turbine to enter sprue and turn stator root to obturage, prevent main flow 1000 ~ 2200K high-temperature fuel gas from pouring in down a chimney and enter turbine disk chamber; Turbine blade prewhirls gas handling system by increasing the tangential velocity entering the inside rotating disc cavities internal gas flow that cover plate and the turbine disk are formed, and the relative stagnation temperature of reduction cooled gas, reaches the effect of better cooling turbine dish and turbine blade.
Find according to a large amount of theoretical and experimental studies: gas is via in inside rotating disc cavities inwardly or outwardly process, due to the Wesco pump effect that rotation roulette is intrinsic, near the fluid rotating card, there is very large tangential velocity, and this can cause the generation of eddy current, cause the very large pressure loss, so be the control to eddy current for the control of coiling chamber flowing at all.
But for the dish chamber of difference in functionality, because the target that will realize is different, the control strategy that needs are taked is not identical yet.
For gas compressor end bleed dish chamber, it is desirable to reduce bleed dish intracavity gas along journey flow losses as far as possible, complete to obturage promoting gas turbine overall efficiency with cooling with less bleed air pressure, bleed temperature, amount of air entrainment, extend the working life of hot-end component.For this purpose, for the inside rotating disc cavities that this radial direction becomes a mandarin, need the control strategy taked to be reduction dish chamber import speed ratio, the development suppressing circumferential eddy currents, reduce the pitot loss because strong circumferential eddy currents causes.
-quiet system dish chamber (the dish chamber be made up of rotation roulette and stator part) turned for turbine, strengthens the cooling effect of the turbine disk, reduce and turn stator root and to obturage required cooling tolerance and to reduce the main flow aerodynamic loss caused due to gas blending of obturaging be the target of coiling chamber flow optimized.Optimizing the strategy taked and be the internal flow of adjustment plate chamber: for forced heat exchanging, by increasing the tangential velocity of cooling-air, reducing the relative stagnation temperature of air-flow; For minimizing mixing loss, the fluid tangential velocity of adjustment plate chamber outlet close to turning, the tangential velocity of position, stator boundary main flow combustion gas.
For turbine blade prewhirl in system turn-transfering from one department to another dish chamber (the dish chamber be made up of the rotor element of two same rotational speed), the tangential velocity of adjustment plate chamber internal gas flow, make the card tangential velocity of the air-flow tangential velocity of turbine blade cooling channel entrance radius therewith identical, reduce inlet flow loss, thus improve blade cooling channel entrance pressure, ensure that blade air conditioning quantity reaches requirement.The control strategy taked is the gas in fin passage is moved to force the mode in whirlpool, ensures that air-flow tangential velocity is equal with local card tangential velocity all the time.
Summary of the invention
The present invention proposes a kind of structure of simple, general control inside rotating disc cavities internal vortex producing and developing.This structure can be used in coiling the centripetal or centrifugal flow in chamber; May be used for turning-quiet system's dish chamber, turn-transfering from one department to another to coil chamber.By the development of control panel chamber internal vortex, realize different targets, as: reduce bleed pitot loss, adjustment axial force, strengthen heat exchange, reduce main flow and Secondary Flow mixing loss etc.
In general, the technological scheme that the present invention adopts for its technical problem of solution is: propose a kind of floor control vortex structure be applied in inside rotating disc cavities.
An aspect according to an embodiment of the invention, propose a kind of floor control vortex structure be arranged in inside rotating disc cavities, comprising: floor, described floor is in the form of a ring; With identical multiple first ribs, be arranged in floor in the face of rotation roulette card first surface on and protrude towards described card, described multiple first rib uniform intervals in the circumferential direction of floor opens layout, and described multiple first rib limits the first air-flow path of navigation between the first surface and described card of floor.
According to the another aspect of the embodiment of the present invention, propose a kind of inside rotating disc cavities system, comprising: centrifugal compressor dish chamber, centrifugal impeller disc portion limits described centrifugal compressor dish chamber; Turbine disk chamber, turbine disk segment limits described turbine disk chamber, wherein: centrifugal compressor dish chamber is communicated with by seal structure with between turbine disk chamber; Be provided with floor control vortex structure at least one in centrifugal compressor dish chamber and turbine disk chamber, this floor control vortex structure comprises: floor, and described floor in the form of a ring; With identical multiple first ribs, be arranged in floor in the face of rotation roulette card first surface on and protrude towards described card, described multiple first rib uniform intervals in the circumferential direction of floor opens layout, and described multiple first rib limits the first air-flow path of navigation between the first surface and described card of floor.
According to the one side again of the embodiment of the present invention, propose a kind of inside rotating disc cavities system, comprise turbine disk chamber, turbine disk segment limits described turbine disk chamber, wherein: in turbine disk chamber, be provided with floor control vortex structure, floor control vortex structure comprises: floor, and described floor in the form of a ring, with identical multiple first ribs, be arranged in floor in the face of rotation roulette card first surface on and protrude towards described card, described multiple first rib uniform intervals in the circumferential direction of floor opens layout, described multiple first rib limits the first air-flow path of navigation between the first surface and described card of floor, described floor control vortex structure is applied to turbine blade cooling and prewhirls in system, described floor is fixed on the wheel disk of turbine as rotation roulette, turbine disk chamber is formed between floor and the card of wheel disk of turbine, described floor is provided with multiple first holes flowing into turbine disk chamber for air-flow, at least one first hole is provided with between the upper adjacent first rib of every a pair circumference.
According to the also one side of the embodiment of the present invention, propose a kind of gas turbine, comprise above-mentioned inside rotating disc cavities system.
Accompanying drawing explanation
Essential characteristic of the present invention by specific embodiments, will carry out more deep explanation by reference to the accompanying drawings.Following specific embodiments is a part of embodiment of the present invention, does not form inappropriate limitation of the present invention.
Fig. 1 be according to one exemplary embodiment of the present invention, floor control vortex structure is applied in sectional view in centrifugal compressor dish chamber and turbine disk chamber, arrow larger in figure specifies main flow flow direction, and comparatively small arrow specifies air system flow path direction.
Fig. 2 is the structural representation according to the floor in the centrifugal compressor dish chamber being applied in Fig. 1 of one exemplary embodiment of the present invention;
Fig. 3 is the schematic perspective view of the floor in Fig. 2;
Fig. 4 be according to another exemplary embodiment of the present invention, floor control vortex structure is applied in sectional view in centrifugal compressor dish chamber and turbine disk chamber;
Fig. 5 be according to exemplary embodiment of the present invention, the structural representation of floor in the centrifugal compressor dish chamber that is applied in Fig. 4;
Fig. 6 be according to exemplary embodiment of the present invention, be applied to centripetal flow dish chamber to strengthen the structural representation of the floor of eddy flow;
Fig. 7 is the structural representation according to the floor in the turbine disk chamber being applied in Fig. 1 of one exemplary embodiment of the present invention;
Fig. 8 be according to one exemplary embodiment of the present invention, be applied in turbine blade cooling and prewhirl the sectional view of the floor control vortex structure in system;
Fig. 9 is the structural representation of floor in Fig. 8.
Embodiment
Below by embodiment, and by reference to the accompanying drawings, technological scheme of the present invention is described in further detail.The explanation of following reference accompanying drawing to embodiment of the present invention is intended to make an explanation to present general inventive concept of the present invention, and not should be understood to one restriction of the present invention.
As shown in Figure 1, the present invention is applied to bleed air stream and turbine disk cooling flowing path, and centrifugal compressor dish chamber 4 is made up of centrifugal impeller dish 1, floor 2, stator casing 3, ring 7 of obturaging; Turbine disk chamber 5 is made up of the turbine disk 9, floor 6 (comprise rib row 11 and arrange 12 with rib), ring 7 of obturaging.
Centrifugal impeller and the turbine disk rotate counterclockwise (seeing from left to right) around running shaft 8, in Fig. 1, comparatively small arrow represents air system path direction: the air of gas compressor sprue enters dish chamber 4 through Centrifugal Impeller Rotor root slit, first the gas entering dish chamber 4 radially-inwardly flow through floor 2, flows into the large chamber of low radius; The gas flowing into large chamber enters turbine disk chamber 5 through seal structure such as comb tooth 10, enters the outwardly flowing through floor 6 and the turbine disk 9 of cooling-air in turbine disk chamber 5, turns stator root enter 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 and comprises: the centrifugal compressor wheel disc in formation dish chamber, with the floor of multi-form rib, the stator casing in formation dish chamber, described centrifugal impeller dish 1 and stator casing form air system tap air channel.
As shown in Figure 1, the mode that floor 2 connects by welding or screw is fixed on stator casing.
Be applied to the dish chamber control strategy that inwardly flows generally to take " subtract and revolve ": subtract and revolve object and be to reduce pitot loss.Take " increasing is revolved " under a few cases, object is to increase radial differential static pressure, reduces card thrust load, and adjustment rotor axial power is in thrust bearing operating range.
Floor is provided with circumferential equally distributed rib on the face of centrifugal impeller side, and rib can be difformity, different deviation angle.The deviation angle of rib refers to the center line of rib and the angle of compressor disk radial direction.On floor, the deflection angle of rib is between 0 degree ~ 90 degree, and when this angle is identical with incoming flow absolute air flow angle, rib passage entrance loss is minimum.Setting has the rib identical with incoming flow absolute air flow angle and can reduce the loss that incoming flow enters rib-rib passage, passage simultaneously between rib and rib can control the development of circumferential eddy currents, by designing the rib of different structure, air-flow is inwardly flowed along rib-rib passage with speed ratio (ratio of the tangential velocity of air-flow and the tangential velocity of the local card) Changing Pattern of design.When speed ratio reduces, eddy flow weakens, and realizes " subtract and revolve "; When speed ratio increases, eddy flow is strengthened, and realizes " increasing is revolved ".For the rib structure for reducing pitot loss being installed on low radius, adjustment rib-rib passage outlet absolute air flow angle is 0 degree, can eliminate the impact of channel outlet flow rotation for the negotiability of downstream flow passage component.
Floor can be arranged on dish chamber height radius or low radius according to different control objectives.When needs reduce along journey pitot loss or increase dish chamber thrust load, floor can be installed on dish chamber high radius, directly reduce the speed ratio of inlet air flow, also can be installed on low radius, have more significantly effect to suppression free vortex; When needs reduce card thrust load, floor is installed on dish chamber high radius, increases airflow inlet speed ratio by floor, the development of enhancing eddy flow, and then increase the radial differential static pressure of card, reduce card middle pressure, final reduction card thrust load.
Rib circumference on floor is uniformly distributed, and fin quantity determines according to the radial position of fin place, ensures that fin row has certain denseness.The final goal that the length of rib can control according to eddy current and dish cavity pressure distributes to be adjusted considers to be selected.Floor can arrange its structure with the arrangement of cantilever pattern in the dish chamber of related application, solves the problem of the lower structure thermal stress release of temperature field effect.
The height of rib is determined by the spacing of floor and rotation roulette card, ensures that the top of rib and rotation roulette spacing are greater than such as 1.0mm, preferably, for 1.5mm to avoid touching mill.But, this spacing is also unsuitable excessive, and to avoid the air-flow non-modulated of more share just to have passed passage between floor and rotation roulette, such as, this spacing can be less than 5mm.The height of rib need ensure enough effective flow areas.
The shape of rib can be straight rib, curved ribs, guide vane form.According to " increasing is revolved " the different objects from " subtract and revolve ", carry out different designs.
Floor 2 concrete structure as shown in Figure 2 and Figure 3.The air entering dish chamber 4 radially inwardly flows in the slit that wheel disc 1 and floor 2 are formed, and rib-rib passages different on floor can control the air radially-inwardly development of circumferential eddy currents in flow process.
Floor 2 can be loaded on high radius as shown in Figure 1, also can be loaded on low radius as shown in Figure 4.The floor being loaded on low radius is nearer because range hadn wheel chamber exports, and has more direct and obvious effect for reduction flow rotation ratio.
On floor 2 shown in Fig. 4, the height of rib is determined according to card curve form, makes rib top and card apart from basically identical, ensures that gas as much as possible is in rib-rib passage.
The entrance angle of floor shown in Fig. 2 α equals radially inwardly moving air import absolute air flow angle, and ω is depicted as centrifugal impeller sense of rotation.Figure 2 shows that simple straight rib structure, rib import rounding, reduces rib-rib passage entrance loss.Rib row also can be designed to guide vane form according to Fig. 5, Fig. 6, and the rib-rib passage outlet flow angle of the floor of form shown in Fig. 5 is 0 degree, substantially for weakening eddy flow; The channel outlet flow angle of the floor of structural type shown in Fig. 6 is that β, β are greater than entrance angle α, for strengthening eddy flow.
Research shows that stream air can cause downstream passage component flow coefficient to reduce when having larger circumferential speed, and as outlet port, centrifugal pan chamber comb tooth 10 in Fig. 1, and this impact is particularly evident to orifice plate.So the floor of structural type shown in Fig. 5 is used for low radius, can not only reduce the pressure loss, can eliminate exit flow circumferential speed affects downstream components simultaneously.
In Fig. 1, floor 6 is in turbine disk chamber 5, installs after floor and originally large turbine disk chamber is become shallow bid chamber, and can reduce turbine disk chamber and turn flow of obturaging needed for stator root, isolated guider inner ring is to the radiative heat transfer of the turbine disk simultaneously.
The main target being arranged at the floor control vortex structure of inside, turbine disk chamber is: forced heat exchanging, strengthens cooled gas to the cooling effect of the turbine disk; Reduce the aerodynamic loss cooling gas of obturaging and when end wall is released into main flow, main flow is caused.The low radius in dish chamber is arranged at for strengthening the rib of cooled gas to turbine disk cooling effect.Be generally positioned at coil chamber high radius for reducing the obturage rib of gas and main flow mixing loss of cooling, by adjustment plate chamber exit flow angle, make the gas leaking into main flow from end wall import main flow combustion gas with the tangential velocity flowing to mouth close to rotor main, reduce mixing loss.Particularly, as shown in Figure 1, floor 6 there is the rib row 11 laying respectively at low radius arrange 12 with the rib of high radius.The rib being positioned at low radius is arranged 11 control strategies and is: adjustment cooling blast angle, makes air-flow tangential velocity increase, thus the relative stagnation temperature of reduction air-flow, forced heat exchanging, compared with traditional preswirl nozzle, the flow field that rib structure obtains is more even, eliminates card localized heat stress and concentrates; The rib being positioned at high radius is arranged 12 control strategies and is: be arranged near turning stator root by rib row 12, the turbine disk cooling-air tangential velocity being about to import main flow is adjusted to close to the tangential velocity of main flow combustion gas herein, reduces the aerodynamic loss that blending causes for main flow.
Fig. 7 is that the rib of low radius arranges 11 concrete structure schematic diagram.Air-flow enters rib row passage with very low tangential velocity, is greatly increased, thus reduces the relative stagnation temperature of air-flow, the heat exchange of the strengthening turbine disk by air-flow tangential velocity after rib row.
In FIG, by installing long floor 6, large dish chamber being divided into loculus, can reducing and turn stator root and to obturage institute's air demand, thus reducing air system amount of air entrainment.
Be analogous to the application of rib in centripetal flow dish chamber, rib import equal with inlet air flow angle at the deflection angle of the turbine disk chamber middle rib of centrifugal flow is carried out rounding, rib circumference on floor and is uniformly distributed and keeps certain denseness.
What floor control vortex structure also can be applicable to that turbine blade prewhirls that system cover plate and the turbine disk formed turn-turns centrifugal flow dish chamber.Turn from turbine-quiet system's dish chamber is different, floor is used for being identical with local card in order to control blade path inlet air flow tangential velocity herein, reduce the blade path inlet air flow pressure loss, improve the pressure of the air being used for blade cooling, ensure that blade cooling tolerance is sufficient.Figure 8 shows that floor another embodiment in the system of dish chamber, rib structure is applied to turbine blade cooling and prewhirls in system by this embodiment.Arrow represents flow of cooling air direction, and the cooling-air flowing to chamber 5 from pre-trepanning 4 is divided into three strands, and one flows into chamber 13 through comb tooth 12 and turns stator root in order to obturage, and prevents main flow high-temperature fuel gas from pouring in down a chimney; One flows out through comb tooth 11 and enters another chamber; One enters turbine disk chamber 6 through receiving hole 9.The cooled gas entered in turbine disk chamber 6 radially flows, and after floor 2, access aperture 10 is in order to cooling turbine bucket.Floor 2 is fixed on rotation roulette 3, pivots together with wheel disc 3.Appropriate design rib row shape, before making access aperture 10, gas tangential velocity therewith radius card tangential velocity is identical, reduces entrance loss.Floor 2 rotates and to the cooling-air work done in rib-rib passage, can increase blade air conditioning quantity simultaneously, ensures blade long-term work under high temperature and high load lotus state.Floor 2 concrete structure as shown in Figure 9, uses straight rib to arrange, and ensures that air-flow speed ratio in rib-rib passage is always 1 the ratio of local card tangential velocity (the air-flow tangential velocity with).
To sum up, the present invention proposes following scheme:
1, be arranged on the floor control vortex structure in inside rotating disc cavities, comprise:
Floor, described floor is in the form of a ring; With
Identical multiple first ribs, be arranged in floor in the face of rotation roulette card first surface on and protrude towards described card, described multiple first rib uniform intervals in the circumferential direction of floor opens layout, and described multiple first rib limits the first air-flow path of navigation between the first surface and described card of floor.
2, according to 1 floor control vortex structure, wherein: the air flow inlet end of first rib is rounded.
3, according to 1 floor control vortex structure, wherein: the spacing between the top of first rib and the card of rotation roulette is between 1.0mm-5.0mm.
4, according to 1 floor control vortex structure, wherein: described floor is arranged on stator casing.
5, according to 4 floor control vortex structure, wherein: the import deflection angle of each first rib is substantially equal to incoming flow absolute air flow angle, the import deflection angle of first rib refers to the center line of the inducer of first rib and the angle of rotation roulette radial direction.
6, according to 4 or 5 floor control vortex structure, wherein: described inside rotating disc cavities is centrifugal compressor dish chamber, and described rotation roulette is centrifugal impeller dish.
7, according to 6 floor control vortex structure, wherein: described first rib is arranged near the radial inner end of wheel disc card.
8, according to 7 floor control vortex structure, wherein: described first rib is curved ribs, and the outlet deflection angle of first rib is roughly 0 degree, and the outlet deflection angle of first rib refers to the center line of the outlet section of first rib and the angle of rotation roulette radial direction.
9, according to 7 floor control vortex structure, wherein: one end of floor is fixed to the support extended in centrifugal compressor dish chamber, and described support is fixed on stator casing.
10, according to 6 floor control vortex structure, wherein: described first rib is arranged near the radial outer end of wheel disc card.
11, according to 5 or 10 floor control vortex structure, wherein: described first rib is curved ribs, and the outlet deflection angle of first rib is greater than described import deflection angle, and the outlet deflection angle of first rib refers to the center line of the outlet section of first rib and the angle of rotation roulette radial direction.
12, according to 10 floor control vortex structure, wherein: described first rib is straight rib.
13, according to 10 floor control vortex structure, wherein: on the stator casing near Centrifugal Impeller Rotor root of one end of floor.
14, according to 5 floor control vortex structure, wherein: described rotation roulette is the turbine disk, described floor extends to the turbine disk and turns near stator root near the seal structure in centrifugal compressor dish chamber, form turbine disk chamber between described floor and the described turbine disk, described turbine disk chamber is communicated with described centrifugal compressor dish chamber by described seal structure.
15, according to 14 floor control vortex structure, wherein: described multiple rib also comprises identical multiple second ribs, be arranged in floor in the face of rotation roulette card first surface on and protrude towards described card, described multiple second rib uniform intervals in the circumferential direction of floor opens layout, and described multiple second rib limits the second air-flow path of navigation between the first surface and described card of floor; Described multiple first rib is arranged in the radial inner end of floor, and at least part of air-flow from seal structure enters the air-flow path between multiple first rib; Described multiple second rib arranges at the radial outer end of floor and turns stator root near the turbine disk, and at least part of air-flow in turbine disk chamber enters combustion gas sprue via the air-flow path between multiple second rib.
16, according to 15 floor control vortex structure, wherein: described first rib is curved ribs, and the outlet deflection angle of first rib is designed to the tangential velocity of the exit flow increasing the air-flow path flowed out between first rib, the outlet deflection angle of first rib refers to the center line of the outlet section of first rib and the angle of rotation roulette radial direction; Described second rib is curved ribs, the radial outer end of second rib turns stator wheel rim near the turbine disk, and the outlet deflection angle of second rib is configured so that the tangential velocity of the exit flow of the air-flow path flowed out between second rib is close with main flow combustion gas tangential velocity, the outlet deflection angle of second rib refers to the center line of the outlet section of second rib and the angle of rotation roulette radial direction.
17, according to 15 floor control vortex structure, wherein: the air flow inlet end of second rib is rounded.
18, according to 14 floor control vortex structure, wherein: described floor is only provided with first rib, one end of first rib is near the radial inner end of floor, and the other end turns stator root near the turbine disk.
19, according to 4 floor control vortex structure, wherein: one end of floor is fixed to stator casing, the other end is free end.
20, according to 1 floor control vortex structure, wherein: described floor control vortex structure is applied to turbine blade cooling and prewhirls in system, described floor is fixed on the wheel disk of turbine as rotation roulette, turbine disk chamber is formed between floor and the card of wheel disk of turbine, described floor is provided with multiple first holes flowing into turbine disk chamber for air-flow, between the upper adjacent first rib of every a pair circumference, is provided with at least one first hole.
21, according to 20 floor control vortex structure, wherein: described first rib is straight rib, the outlet deflection angle of first rib is roughly 0 degree, and the outlet deflection angle of first rib refers to the center line of first rib and the angle of wheel disk of turbine radial direction.
22, according to 21 floor control vortex structure, wherein: between the upper adjacent first rib of every a pair circumference, be provided with first hole, the first all holes is arranged at equal intervals along a circumference, the circumference at the place, radial inner end extend through first hole of each first rib, the radial outer end of each first rib is near turbine blade cooling channel entrance.
23, an inside rotating disc cavities system, comprising: centrifugal compressor dish chamber, and centrifugal impeller disc portion limits described centrifugal compressor dish chamber; Turbine disk chamber, turbine disk segment limits described turbine disk chamber, wherein: centrifugal compressor dish chamber is communicated with by seal structure with between turbine disk chamber; The floor control vortex structure any one of 1-5,19 is provided with at least one in centrifugal compressor dish chamber and turbine disk chamber.
24, according to 23 inside rotating disc cavities system, wherein: in centrifugal compressor dish chamber, be provided with the floor control vortex structure according to any one of claim 6-13.
25, according to 23 or 24 inside rotating disc cavities system, wherein: in turbine disk chamber, be provided with the floor control vortex structure according to any one of claim 14-18.
26, an inside rotating disc cavities system, comprises turbine disk chamber, and turbine disk segment limits described turbine disk chamber, wherein: be provided with the floor control vortex structure any one of 20-22 in turbine disk chamber.
27, a gas turbine, comprises the inside rotating disc cavities system any one of 23-26.
Floor control vortex structure of the present invention by installing the floor with rib in dish chamber, and regulate and control the eddy current producing and developing in dish chamber, this invention at least tool one of has the following advantages:
1., structure is simple, is highly susceptible to realizing.Simple rib structure, is easy to processing and installs, lightweight, can avoid vibration problem because floor is installed on (a few cases is also installed in rotor element) on stator part simultaneously.
2., on floor the form of rib is changeable, is designed to straight rib, curved ribs, guide vane form rib as required.
3., rib structure is widely used.This rib structure can be applied to the centripetal or centrifugal flow in dish chamber.Minimizing dish chamber bleed pitot loss can be realized; The thrust load that the distribution of adjustment plate chamber internal pressure thus adjustment rotor thrust bearing bear; Adjustment plate chamber internal cooling air-flow angle, thus reduce relative stagnation temperature, strengthen heat exchange; Adjustment plate chamber turns stator root leakage flow tangential velocity and turbine rotor import main flow tangential velocity is close, reduces mixing loss.
4., floor can play heat insulation effect.The floor being installed on centrifugal back of the body chamber can completely cut off the conduction of firing chamber heat, the floor being installed on turbine disk chamber can completely cut off the heat conduction of combustor exit high temperature stator casing for the turbine disk, and floor is thin-slab structure, one end is free end, can free expansion, different temperatures can be solved and divide the release And Spread of Solute planting structure thermal stress.
In addition, it should be noted that, the specific embodiment described in this specification, the shape, institute's title of being named etc. of its parts and components can be different.All equivalences of doing according to structure, feature and the principle described in inventional idea of the present invention or simple change, be included in the protection domain of patent of the present invention.Those skilled in the art can make various amendment or supplement or adopt similar mode to substitute to described specific embodiment; only otherwise depart from structure of the present invention or surmount this scope as defined in the claims, protection scope of the present invention all should be belonged to.
Claims (27)
1. be arranged on the floor control vortex structure in inside rotating disc cavities, comprise:
Floor, described floor is in the form of a ring; With
Identical multiple first ribs, be arranged in floor in the face of rotation roulette card first surface on and protrude towards described card, described multiple first rib uniform intervals in the circumferential direction of floor opens layout, and described multiple first rib limits the first air-flow path of navigation between the first surface and described card of floor.
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:
Described floor is arranged on stator casing.
5. floor control vortex structure according to claim 4, wherein:
The import deflection angle of each first rib is substantially equal to incoming flow absolute air flow angle, and the import deflection angle of first rib refers to the center line of the inducer of first rib and the angle of rotation roulette radial direction.
6. the floor control vortex structure according to claim 4 or 5, wherein:
Described inside rotating disc cavities is centrifugal compressor dish chamber, and described rotation roulette is centrifugal impeller dish.
7. floor control vortex structure according to claim 6, wherein:
Described first rib is arranged near the radial inner end of wheel disc card.
8. floor control vortex structure according to claim 7, wherein:
Described first rib is curved ribs, and the outlet deflection angle of first rib is roughly 0 degree, and the outlet deflection angle of first rib refers to the center line of the outlet section of first rib and the angle of rotation roulette radial direction.
9. floor control vortex structure according to claim 7, wherein:
One end of floor is fixed to the support extended in centrifugal compressor dish chamber, and described support is fixed on stator casing.
10. floor control vortex structure according to claim 6, wherein:
Described first rib is arranged near the radial outer end of wheel disc card.
11. floor control vortex structures according to claim 5 or 10, wherein:
Described first rib is curved ribs, and the outlet deflection angle of first rib is greater than described import deflection angle, and the outlet deflection angle of first rib refers to the center line of the outlet section of first rib and the angle of rotation roulette radial direction.
12. floor control vortex structures according to claim 10, wherein:
Described first rib is straight rib.
13. floor control vortex structures according to claim 10, wherein:
On the stator casing near Centrifugal Impeller Rotor root of one end of floor.
14. floor control vortex structures according to claim 5, wherein:
Described rotation roulette is the turbine disk, described floor extends to the turbine disk and turns near stator root near the seal structure in centrifugal compressor dish chamber, form turbine disk chamber between described floor and the described turbine disk, described turbine disk chamber is communicated with described centrifugal compressor dish chamber by described seal structure.
15. floor control vortex structures according to claim 14, wherein:
Described multiple rib also comprises identical multiple second ribs, be arranged in floor in the face of rotation roulette card first surface on and protrude towards described card, described multiple second rib uniform intervals in the circumferential direction of floor opens layout, and described multiple second rib limits the second air-flow path of navigation between the first surface and described card of floor;
Described multiple first rib is arranged in the radial inner end of floor, and at least part of air-flow from seal structure enters the air-flow path between multiple first rib;
Described multiple second rib arranges at the radial outer end of floor and turns stator root near the turbine disk, and at least part of air-flow in turbine disk chamber enters combustion gas sprue via the air-flow path between multiple second rib.
16. floor control vortex structures according to claim 15, wherein:
Described first rib is curved ribs, and the outlet deflection angle of first rib is designed to the tangential velocity of the exit flow increasing the air-flow path flowed out between first rib, the outlet deflection angle of first rib refers to the center line of the outlet section of first rib and the angle of rotation roulette radial direction;
Described second rib is curved ribs, the radial outer end of second rib turns stator wheel rim near the turbine disk, and the outlet deflection angle of second rib is configured so that the tangential velocity of the exit flow of the air-flow path flowed out between second rib is close with main flow combustion gas tangential velocity, the outlet deflection angle of second rib refers to the center line of the outlet section of second rib and the angle of rotation roulette radial direction.
17. floor control vortex structures according to claim 15, wherein:
The air flow inlet end of second rib is rounded.
18. floor control vortex structures according to claim 14, wherein:
Described floor is only provided with first rib, and one end of first rib is near the radial inner end of floor, and the other end turns stator root near the turbine disk.
19. floor control vortex structures according to claim 4, wherein:
One end of floor is fixed to stator casing, and the other end is free end.
20. floor control vortex structures according to claim 1, wherein:
Described floor control vortex structure is applied to turbine blade cooling and prewhirls in system, described floor is fixed on the wheel disk of turbine as rotation roulette, turbine disk chamber is formed between floor and the card of wheel disk of turbine, described floor is provided with multiple first holes flowing into turbine disk chamber for air-flow, between the upper adjacent first rib of every a pair circumference, is provided with at least one first hole.
21. floor control vortex structures according to claim 20, wherein:
Described first rib is straight rib, and the outlet deflection angle of first rib is roughly 0 degree, and the outlet deflection angle of first rib refers to the center line of first rib and the angle of wheel disk of turbine radial direction.
22. floor control vortex structures according to claim 21, wherein:
First hole is provided with between the upper adjacent first rib of every a pair circumference, the first all holes is arranged at equal intervals along a circumference, the circumference at the place, radial inner end extend through first hole of each first rib, the radial outer end of each first rib is near turbine blade cooling channel entrance.
23. 1 kinds of inside rotating disc cavities systems, comprising:
Centrifugal compressor dish chamber, centrifugal impeller disc portion limits described centrifugal compressor dish chamber;
Turbine disk chamber, turbine disk segment limits described turbine disk chamber,
Wherein:
Centrifugal compressor dish chamber is communicated with by seal structure with between turbine disk chamber;
The floor control vortex structure according to any one of claim 1-5,19 is provided with at least one in centrifugal compressor dish chamber and turbine disk chamber.
24. inside rotating disc cavities systems according to claim 23, wherein:
The floor control vortex structure according to any one of claim 6-13 is provided with in centrifugal compressor dish chamber.
25. inside rotating disc cavities systems according to claim 23 or 24, wherein:
The floor control vortex structure according to any one of claim 14-18 is provided with in turbine disk chamber.
26. an inside rotating disc cavities system, comprise turbine disk chamber, turbine disk segment limits described turbine disk chamber, wherein: be provided with the floor control vortex structure according to any one of claim 20-22 in turbine disk chamber.
27. 1 kinds of gas turbines, comprise the inside rotating disc cavities system according to any one of claim 23-26.
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 |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611258387.6A Division CN106677903B (en) | 2015-04-30 | 2015-04-30 | Floor control vortex structure, inside rotating disc cavities system, gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105402028A true CN105402028A (en) | 2016-03-16 |
| CN105402028B CN105402028B (en) | 2017-05-03 |
Family
ID=55467739
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510214714.7A Active CN105402028B (en) | 2015-04-30 | 2015-04-30 | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine |
| CN201611258387.6A Active CN106677903B (en) | 2015-04-30 | 2015-04-30 | Floor control vortex structure, inside rotating disc cavities system, gas turbine |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611258387.6A Active CN106677903B (en) | 2015-04-30 | 2015-04-30 | Floor control vortex structure, inside rotating disc cavities system, gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN105402028B (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105888850A (en) * | 2016-06-12 | 2016-08-24 | 贵州航空发动机研究所 | Blade type pre-swirl nozzle with rectification rib |
| CN106640739A (en) * | 2016-12-24 | 2017-05-10 | 中国科学院工程热物理研究所 | Adjustable centrifugal compressor circular seam air-entraining structure |
| CN107131009A (en) * | 2017-05-16 | 2017-09-05 | 中国科学院工程热物理研究所 | A kind of turbomachine self-locking seal structure and the engine with it |
| CN107725479A (en) * | 2017-09-26 | 2018-02-23 | 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 |
| CN109555603A (en) * | 2017-09-27 | 2019-04-02 | 中国航发商用航空发动机有限责任公司 | A kind of composite material sealing cover and preparation method thereof |
| CN110318874A (en) * | 2019-06-24 | 2019-10-11 | 中国科学院工程热物理研究所 | The control whirlpool flow path system of centrifugal compressor back chamber in a kind of gas turbine |
| CN110552788A (en) * | 2019-09-19 | 2019-12-10 | 西北工业大学 | Cover plate disc with radial runway inclined hole type receiving hole for pre-rotation gas supply system |
| 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 |
| CN111963320A (en) * | 2020-08-24 | 2020-11-20 | 浙江燃创透平机械股份有限公司 | Gas turbine interstage seal ring structure |
| 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 |
| CN113123999A (en) * | 2021-03-26 | 2021-07-16 | 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 |
| CN113217120A (en) * | 2020-01-21 | 2021-08-06 | 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 aircraft engine |
| CN113357189A (en) * | 2021-06-23 | 2021-09-07 | 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 |
| CN113495001A (en) * | 2020-04-02 | 2021-10-12 | 中国航发商用航空发动机有限责任公司 | Device and method for measuring entrainment flow ratio of disk cavity of gas compressor |
| CN114151141A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Aeroengine turbine disc cavity gas collection water conservancy diversion structure |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110726690B (en) * | 2019-10-11 | 2022-05-06 | 中国航发沈阳发动机研究所 | Multi-branch turbine disc cavity flow measurement structure and measurement method |
| CN111927561A (en) * | 2020-07-31 | 2020-11-13 | 中国航发贵阳发动机设计研究所 | Rotary pressurizing structure for cooling turbine blade |
| 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 |
| CN112983648B (en) * | 2021-04-13 | 2022-04-01 | 浙江大学 | Gas turbine radial air inlet chamber flow active control device |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2834753B1 (en) * | 2002-01-17 | 2004-09-03 | Snecma Moteurs | TURBOMACHINE AXIAL COMPRESSOR DISC WITH CENTRIPTED AIR TAKE-OFF |
| CN103867235B (en) * | 2012-12-18 | 2015-12-23 | 中航商用航空发动机有限责任公司 | A kind of tubular type subtracts whirlpool device bleed air system |
| EP2826957A1 (en) * | 2013-07-17 | 2015-01-21 | Siemens Aktiengesellschaft | Rotor for a thermal turbomachine |
| CN203685310U (en) * | 2013-12-11 | 2014-07-02 | 中航商用航空发动机有限责任公司 | Air entraining structure of eddy reduction device |
| CN104196572B (en) * | 2014-07-15 | 2016-07-13 | 西北工业大学 | A kind of double; two disc turbine disks with dish chamber diversion rib plate |
-
2015
- 2015-04-30 CN CN201510214714.7A patent/CN105402028B/en active Active
- 2015-04-30 CN CN201611258387.6A patent/CN106677903B/en active Active
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105888850A (en) * | 2016-06-12 | 2016-08-24 | 贵州航空发动机研究所 | Blade type pre-swirl nozzle with rectification rib |
| CN106640739A (en) * | 2016-12-24 | 2017-05-10 | 中国科学院工程热物理研究所 | Adjustable centrifugal compressor circular seam air-entraining 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 |
| CN107131009A (en) * | 2017-05-16 | 2017-09-05 | 中国科学院工程热物理研究所 | A kind of turbomachine self-locking seal structure 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 |
| CN107725479A (en) * | 2017-09-26 | 2018-02-23 | 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 |
| CN109555603A (en) * | 2017-09-27 | 2019-04-02 | 中国航发商用航空发动机有限责任公司 | A kind of composite material sealing cover and preparation method thereof |
| 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 |
| CN110318874A (en) * | 2019-06-24 | 2019-10-11 | 中国科学院工程热物理研究所 | The control whirlpool flow path system of centrifugal compressor back chamber in a kind of gas turbine |
| 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 |
| CN110552788A (en) * | 2019-09-19 | 2019-12-10 | 西北工业大学 | Cover plate disc with radial runway inclined hole type receiving hole for pre-rotation gas supply system |
| CN113217120A (en) * | 2020-01-21 | 2021-08-06 | 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 aircraft engine |
| 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 |
| CN113495001A (en) * | 2020-04-02 | 2021-10-12 | 中国航发商用航空发动机有限责任公司 | Device and method for measuring entrainment flow ratio of disk cavity of gas compressor |
| CN113495001B (en) * | 2020-04-02 | 2022-06-21 | 中国航发商用航空发动机有限责任公司 | Device and method for measuring entrainment flow ratio of disk cavity of gas compressor |
| CN111963320A (en) * | 2020-08-24 | 2020-11-20 | 浙江燃创透平机械股份有限公司 | Gas turbine interstage seal ring structure |
| 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 |
| CN113123998A (en) * | 2021-03-26 | 2021-07-16 | 北京航空航天大学 | Compressor conical wall cavity for inhibiting vortex formation |
| CN113123999A (en) * | 2021-03-26 | 2021-07-16 | 北京航空航天大学 | Shunting cooling type aero-engine compressor rear shaft diameter conical wall cavity |
| 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 |
| CN113357189A (en) * | 2021-06-23 | 2021-09-07 | 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 |
| CN114151141A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Aeroengine turbine disc cavity gas collection water conservancy diversion structure |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106677903A (en) | 2017-05-17 |
| CN105402028B (en) | 2017-05-03 |
| CN106677903B (en) | 2018-07-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105402028A (en) | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine | |
| JP5279400B2 (en) | Turbomachine diffuser | |
| EP3026240B2 (en) | Gas turbine engine with partial inlet vane | |
| CN101333937B (en) | Device for cooling the cavities of a turbomachine rotor disc | |
| US10526906B2 (en) | Mobile turbine blade with an improved design for an aircraft turbomachine | |
| JP5507828B2 (en) | Asymmetric flow extraction system | |
| CN110030045B (en) | Turbine engine with annular cavity | |
| US10082031B2 (en) | Rotor of a turbine of a gas turbine with improved cooling air routing | |
| US5791136A (en) | Combined-cycle power generation plant, including a gas turbine, an annual exhaust gas channel having swirl suppression vanes, and a heat recovery boiler | |
| US7465149B2 (en) | Turbine engine cooling | |
| JP2017526845A (en) | Turbine blades with optimized cooling | |
| KR20110065559A (en) | Turbine cooling system | |
| EP2943726B1 (en) | Air handling unit | |
| CN106014645A (en) | Engine component | |
| EP2896787B1 (en) | Gas turbine | |
| CN204312137U (en) | Turbogenerator and turbomachine injection nozzle wheel blade section | |
| CN102116317A (en) | System and apparatus relating to compressor operation in turbine engines | |
| US11118475B2 (en) | Turbine shroud cooling | |
| US8790073B2 (en) | Gas turbine engine including a stator vane for directing hot combustion gases onto rotor blades | |
| US9664204B2 (en) | Assembly for a fluid flow machine | |
| WO2015089048A1 (en) | Swirling midframe flow for gas turbine engine having advanced transitions | |
| US10724391B2 (en) | Engine component with flow enhancer | |
| US10774664B2 (en) | Plenum for cooling turbine flowpath components and blades | |
| US11008871B2 (en) | Turbine blade of a turbine blade ring | |
| US10718267B2 (en) | Turbine engine cooling with substantially uniform cooling air flow distribution |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |