CN109707515A - A kind of vane type wheeling disk structure for gas turbine lubricant passage way system - Google Patents
A kind of vane type wheeling disk structure for gas turbine lubricant passage way system Download PDFInfo
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- CN109707515A CN109707515A CN201811472856.3A CN201811472856A CN109707515A CN 109707515 A CN109707515 A CN 109707515A CN 201811472856 A CN201811472856 A CN 201811472856A CN 109707515 A CN109707515 A CN 109707515A
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Abstract
The present invention provides a kind of vane type wheeling disk structures for gas turbine lubricant passage way system, gas turbine lubricant passage way system includes bearing bore, lubricating cavity and the vane type wheel disc being disposed there between, bearing bore is interconnected by vane type wheel disc and lubricating cavity, multiple water conservancy diversion prismatic blades are uniformly arranged in the circumferential direction between the central tube and ring bodies of vane type wheel disc, space between adjacent two water conservancy diversion prismatic blade forms drainback passage, the cross section of each water conservancy diversion prismatic blade is wing, so that there is slanted angle between the leading edge of water conservancy diversion prismatic blade and axial incoming flow and incoming flow is avoided to occur flow separation at trailing edge.Used lubricating oil flows into lubricating cavity by each drainback passage from bearing bore.Vane type wheeling disk structure of the invention realizes the foundation of relatively stable pressure difference between bearing bore and lubricant reservoir while realizing wheel disc loss of weight, guarantees the stability of oil return and has achieved the purpose that lubricating oil supply high efficiency and engine performance driving economy.
Description
Technical field
The present invention relates to Gas Turbine fields, especially aero-turbine field, are in whirlpool more specifically
In the lubricating oil return system of wheel, using Novel impeller type wheeling disk structure, lubricant passage way oil return smoothness is effectively improved, simultaneously
Reduce wheel disc quality, and then improves the safety and engine performance of turbine operation.
Background technique
The modern aeroengine basic element of character mainly includes air intake duct, compressor, combustion chamber, turbine and jet pipe.Air
Enter in compressor after air intake duct rectifies and compressed, pressure-air fuel oil is blended in combustion chambers burn later, generates high temperature
High-pressure gas red switch turbine does work, and the combustion gas after turbine expansion increases motor power by jet pipe.The function one that turbine generates
Aspect provides engine power, on the one hand provides the work done during compression of compressor.
In the process, compressor and turbine are in high speed rotation state always.To guarantee engine work, it is necessary to
It plays a supportive role using to engine, and bears the bearing of certain axial force.In order to reduce bearing friction, take away by rubbing surface institute
The heat and abrasion impurity of generation simultaneously guarantee that bearing inner race is adequately cooled, and effectively reduce high-speed bearing inner ring and rub and hurt failure
Probability, being lubricated to bearing is the most important link for guaranteeing the safe and reliable operation of bearing.For shaft in engine and axis
The complexity problem that value volume and range of product increases bring bearing arrangement and bearing oil system is held, how succinctly effective arrangement bearing
And corresponding oil system pipeline, have very important significance for the high efficiency tool of engine operation.
Chinese patent application CN201510219735.8 discloses a kind of for being adjacently positioned at least two on center shaft
The lubricant passage way system of a bearing, the lubricant reservoir of at least two bearing lubricating oil circuits are total to chamber and arrange, and at least two bearings
Lubricating oil flows to common lubricating oil return mouth.In order to simplify bearing lubrication oil system, the turbine disk is as low-pressure turbine disk disk
The heart realizes the fuel feeding by lubricant reservoir to bearing bore to the interface channel between bearing bore and lubricant reservoir.Specifically, as Fig. 1,
Shown in 2, the lubricant reservoir 601 of the lubricant passage way of the lubricant passage way and second bearing 301 of first bearing 302 is total to chamber arrangement, lubrication
The top of oil pocket 601 is connected to oil gas vent 203, and the lower part of lubricant reservoir 601 is connected to lubricating oil return mouth 204, from the
One bearing 302 and the lubricating oil of second bearing 301 flow to lubricating oil return mouth 204.Engine operation when, lubricating oil from into
Oil pipe line fuel oil supply nozzle 201 enters in the oil supplying sleeve 202 in low pressure shaft tail end, then by the nozzle opening being distributed on low-pressure shaft,
The first and second bearing 301,302 is lubricated and is cooled down from inner ring respectively.Used lubricating oil enters in bearing bore 403, and
Collect on the inner wall for preceding obturaging ring 401.Before to obturage the inner wall of ring 401 be the conically shaped with gradient, lubricating oil exists
It under gravity, is flowed backward along ring inner wall is preceding obturaged, the conically shaped 101 flowed on T-type disk is located at inclined shore floor 106
In front half section 102 before.The annular for being set to 102 fronts, which is kept off before oily boss 104 can prevent lubricating oil from passing through, obturages ring tail
The circular passage 403 at end enters low-pressure turbine disk chamber, prevents oil leakage.Flow into 102 inner wall of T-type discone cylinder front half section
On lubricating oil by be distributed in T-type disk tilt thin-walled 106 on fan-shaped drainback passage 105 flow into the T-type discone cylinder second half section
103, and continue to flow backward, subsequently into oil return line 204.In engine actual motion, full of profit in bearing bore 401
Lubricating oil and oil gas.Because lubricating oil viscosity is larger, the lubricating oil flowed out from bearing can be attached on T-type disk, in centrifugal force
Under effect, the inclined wall on T-type disk can play the role of " oil mist separator ", and the lubricating oil for being attached to T-type panel surface is got rid of
Onto the conically shaped inner wall of T-type disk, converge with lubricating oil mainstream.Meanwhile under the influence of centrifugal force, inclined conically shaped inner wall
It is also beneficial to the reflux of lubricating oil.In engine operation, lubricating oil and oil gas are also filled in lubricant reservoir 601.By T-type
The conically shaped larger of disk, can expand the space in lubricant reservoir, be conducive to the separation of lubricating oil and oil gas.Divide completely
Oil gas from after can be flowed out from oil and gas pipeline 203, and lubricating oil then enters in lubricating oil return pipeline 204, avoids lubricating oil
Air-fuel mixture in oil return line is unfavorable for lubricating oil recycling.Connected between the central tube and ring bodies of the T-type impeller disk using floor
It connecing, central tube 108 is socketed on the end of central axis, and adjacent floor is spaced apart in a circumferential direction and forms void openings, or
Person's floor is Circular plate structure, and Circular plate structure is opened close to multiple gaps that ring bodies is provided with along the circumferential direction equidistant apart
Mouthful；Ring bodies has the axially inner side cylinder and axially external cylinder being spaced apart by floor, and the lubricating oil from bearing bore 401 successively passes through
By the inner surface of axially inner side cylinder, void openings, axially external cylinder inner surface and reach lubricating oil return mouth.
The turbine T-type impeller disk of above-mentioned simplification disclosed in Chinese patent application CN201510219735.8 has been connected to bearing
Lubricating oil system, while alleviating wheel disc weight and simplifying bearing lubrication oil system.But such rib structure can not be at it
Inlet and outlet play the role of increase it is stressed, the variation of pressure cannot be brought, also can not just establish bearing bore and lubricant reservoir
Between pressure difference, cause lubricant reservoir fuel feeding wild effect occur.Therefore it is remained unchanged in the overall structure of lubricating oil system
In the case where, a kind of novel wheeling disk structure for ensuring lubricating oil supply smoothness and high efficiency is needed, bearing bore 402 and lubricating oil are made
Stable pressure difference is set up between chamber 601.
Summary of the invention
For the disadvantages mentioned above and deficiency of the prior art, the present invention is intended to provide a kind of be used for gas turbine especially aviation
The Novel impeller type wheeling disk structure of the lubricant passage way system of the adjacent bearing of multistage (multiaxis), can effectively eliminate lubricating oil in engine
Chamber fuel feeding wild effect makes to set up stable pressure difference between bearing bore and lubricant reservoir, so as to improve lubricant passage way oil return
Smoothness and high efficiency, while reducing wheel disc quality, improve the safety and engine performance of turbine operation.
To realize the target, the technical solution adopted by the present invention are as follows:
A kind of vane type wheeling disk structure for gas turbine lubricant passage way system, wherein
The gas turbine lubricant passage way system includes vane type wheel disc on centrally disposed axis and is arranged described
The bearing bore of vane type wheel disc upstream, the lubricating cavity that vane type wheel disc downstream is arranged in, the bearing bore pass through the leaf
Wheeled wheel disc and the lubricating cavity are interconnected,
The vane type wheel disc includes coaxially arranged a central tube and a ring bodies, and the central tube is fixedly attached to institute
It states on central axis, the ring bodies is integrally in a cylindrical part, and the outer wall fixation of the ring bodies is set in the one of gas turbine
In the centre bore of the impeller disk, the impeller disk is compressor disc or the turbine disk, and the inner wall of the ring bodies is equipped with an annular branch
Wall is supportted,
It is characterized in that,
The annular support wall and the axial position of the central tube are at least substantially identical, and circumferentially uniform therebetween
Multiple water conservancy diversion prismatic blades are set, and the space between adjacent two water conservancy diversion prismatic blade forms drainback passage, the lubrication in the bearing bore
Oil is flowed into the lubricant reservoir by each drainback passage of the vane type wheel disc, and the cross section of each guide vane is the wing
Shape, the selection of aerofoil profile parameter is not so that by the flowing in each drainback passage apparent segregation phenomenon is occurring for incoming flow.
Vane type wheeling disk structure for gas turbine lubricant passage way system of the invention, its working principle is that, engine
When operation, the vane type wheel disc of rotation can play pressurization to working medium, by bearing bore lubricating oil and mist of oil be drawn into
On the one hand oil return lubricating cavity ensure that the lubricating oil in bearing bore is taken away in time, will not oil accumulation, on the other hand reduce in bearing bore
The supply pressure of lubricating oil, is conducive to lubricating oil supply, and the third aspect improves the lubricating oil return pressure in lubricating cavity, is conducive to lubricating oil
Recycling.
More preferably, the central tube is fixed on the central axis by card slot and screw, each water conservancy diversion prismatic blade
Knuckle is provided with the junction of the annular support wall and central tube.
More preferably, the junction of the annular support wall and the ring bodies inner wall is provided with knuckle.
More preferably, the inner wall of the ring bodies is divided into front half section and second half section by the annular support wall, described later half
Section has the tilt angle expanded outwardly.Preferably, the tilt angle is 5~15 °.
More preferably, the quantity of the water conservancy diversion prismatic blade is according to the design pressure difference and profit between the bearing bore and lubricant reservoir
Lubricating oil amount determines.
More preferably, the return flow line can adjust the relationship of flow and stability with partial-air admission mode.
More preferably, the aerofoil profile leading edge of the water conservancy diversion prismatic blade uses thickness appropriate and stagger angle, and blade trailing edge is adopted
With small as far as possible thickness and exit installation angle appropriate, to guarantee blade strength requirement and avoid trailing edge flow separation.
Compared with the existing technology, vane type wheeling disk structure of the invention efficiently solves to go out between bearing bore and lubricating cavity
Existing oil return has some setbacks and instability problem, realizes the foundation of relatively stable pressure difference between bearing bore and lubricant reservoir, guarantees
The stability of fuel feeding and oil return；The torsion pass and supporting role of turbine are not only met using vane type wheeling disk structure, while hollow
Structure not only realizes wheel disc loss of weight under conditions of meeting intensity, but also has reached lubricating oil supply high efficiency and engine economical operation
The purpose of property.
Detailed description of the invention
Fig. 1 is the gas turbine lubricant passage way system schematic diagram of the prior art；
Fig. 2 is the B direction view of T-type disk in Fig. 1；
Fig. 3 is vane type wheel disc B direction view of the invention；
Fig. 4 is the H-H cross-sectional view of vane type wheel disc in Fig. 3；
Fig. 5 is the C-C blade profile cross-sectional view of vane type wheel disc in Fig. 3.
Specific embodiment
The present invention will be further described in detail below with reference to the embodiments, following embodiment be explanation of the invention and
The invention is not limited to following embodiments.
Fig. 3~5 show the vane type wheeling disk structure suitable for gas turbine lubricant passage way system of the invention, Cong Tuzhong
As can be seen that vane type wheel disc of the invention includes coaxially arranged a central tube 101 and a ring bodies 102, central tube 101 is logical
It crosses card slot and screw is fixedly attached on the central axis of a gas turbine, whole ring bodies 102 is in a cylindrical part, ring bodies
Outer wall fixation is set in the centre bore of an impeller disk of gas turbine, and the impeller disk is compressor disc or the turbine disk, ring bodies 102
Inner wall be equipped with an annular support wall 103, and the junction of annular support wall and ring bodies inner wall is provided with knuckle.Ring
Shape supporting walls 103 and the axial position of central tube 101 are essentially identical, and are uniformly arranged in the circumferential direction the straight leaf of multiple water conservancy diversion therebetween
The junction of piece 106, each water conservancy diversion prismatic blade and annular support wall and central tube is provided with knuckle, and adjacent two water conservancy diversion is straight
Space between blade 106 forms drainback passage, and the cross section of each water conservancy diversion prismatic blade 106 is wing, wing edge tool
There is stagger angle, there is exit installation angle at trailing edge, so that there is inclination between the leading edge of water conservancy diversion prismatic blade and axial incoming flow
Angle simultaneously avoids incoming flow from occurring flow separation at trailing edge.Above-mentioned vane type wheeling disk structure of the invention, the lubrication in bearing bore
Oil can flow into lubricant reservoir by each drainback passage of the vane type wheel disc.When engine is run, the vane type wheel disc of rotation
More stable pressure difference can be established between bearing bore and lubricating cavity, made the lubricating oil in bearing bore without blocking, smoothly flowed into and slide
Oil pocket.
Further, the blade of water conservancy diversion prismatic blade 106 or three-dimensional torsional, quantity, height, shape and venturi face
Product, can determine according to the pressure difference of bearing bore and lubricant reservoir, required lubricants capacity according to turbomachinery design.Blade path
The relationship of flow and stability can be adjusted with partial-air admission mode.Blade path can also be taken from the horizontal by certain
What the inclination of angle was flows to shape.Vane airfoil profile leading edge uses thickness appropriate and stagger angle, and blade trailing edge is using to the greatest extent
Small thickness and exit installation angle appropriate are measured, requires and avoid trailing edge flow separation with proof strength.
More preferably, the inner wall of the ring bodies is divided into front half section 105 and second half section 107, institute by the annular support wall
Stating the second half section 107 has 5~15 ° of the tilt angle expanded outwardly.
Above-mentioned vane type wheeling disk structure of the invention can more preferably be suitable for existing gas turbine lubricating oil shown in FIG. 1
In the system of road, only T-type disk 101 therein need to be replaced using vane type wheeling disk structure of the invention.In Fig. 1,201 be fuel feeding
Nozzle, 202 be oil supplying sleeve, and 203 be oil gas exhaust pipe, and 204 be oil return line；301 be low pressure rear bearing, and 302 is after high pressures
Bearing；401 be before obturage ring, 402 be preceding floating type graphite seal structure, and 403 be bearing bore, 404 be before obturage ring tail end
Circular passage；501 be rear floating type graphite seal structure, 502 be after obturage ring；601 be lubricating cavity；602 be end cap.Dotted line arrow
Head indicates the fuel feeding route (schematic diagram) of lubricating oil.When engine is run, the lubricating oil of bearing is lubricated from oil system fuel oil supply nozzle 201
Into in the oil supplying sleeve 202 in low pressure shaft tail end, then by the nozzle opening being distributed on low-pressure shaft, respectively from high pressure rear bearing
302 and the inner ring of low pressure rear bearing 301 bearing is lubricated and is cooled down, realize fuel feeding under ring.Used lubricating oil is from axis
Middle outflow is held, into bearing bore 403, before the oily boss 104 of annular gear can prevent the lubricating oil in conically shaped front half section 105 from passing through
The circular passage 404 for obturaging ring tail end enters low-pressure turbine disk chamber (as shown in Figure 3,4), prevents lubricating oil from revealing.Flow into bearing bore
Lubricating oil in 403 flows into 601 (lubricating cavity of lubricating cavity by being distributed in the three-dimensional blades channel 106 of 103 inside of impeller disk supporting walls
It is made of conically shaped second half section 107 and end cap 602), and continue to flow backward, subsequently into oil return line 204.In centrifugal force
Under the action of, inclined conically shaped inner wall is conducive to the reflux (as shown in Figure 3) of lubricating oil.
When engine is run, lubricating oil and oil gas are full of in lubricating cavity 601.Oil gas by Oil-gas Separation, after being kept completely separate
It is flowed out by oil and gas pipeline 203, lubricating oil then passes through the discharge of scavenge oil line road 204, and it is mixed to avoid oil gas in scavenge oil line road
It closes, is unfavorable for the recycling of lubricating oil.To avoid the oil gas in bearing bore and lubricating cavity from entering turbine disk chamber, the two of impeller disk outer ring
End and forward and backward obturage are equipped with floating type graphite seal structure 402 and 501 between ring.Selectively, which can also adopt
It is obturaged with castor tooth, other seal structures such as contact graphite seal or brush seal.
In addition, it should be noted that, the specific embodiments described in this specification, shape, name of parts and components etc.
It can be different.It is all according to principle described in the invention patent and to conceive the equivalent or simple change of done construction, feature, include
In in the scope of protection of the patent of the present invention.Those skilled in the art can be to described specific embodiment
Various modifications are done, supplements or is substituted in a similar manner, without departing from structure of the invention or surmount present claims
Range defined in book, is within the scope of protection of the invention.
Claims (9)
1. a kind of vane type wheeling disk structure for gas turbine lubricant passage way system, wherein
The gas turbine lubricant passage way system includes vane type wheel disc on centrally disposed axis and is arranged in the impeller
The bearing bore of formula wheel disc upstream, the lubricating cavity that vane type wheel disc downstream is arranged in, the bearing bore pass through the vane type
Wheel disc and the lubricating cavity are interconnected,
The vane type wheel disc includes coaxially arranged a central tube and a ring bodies, and the central tube is fixedly attached in described
In mandrel, the ring bodies is integrally in a cylindrical part, the fixed impeller for being set in gas turbine of the outer wall of the ring bodies
In the centre bore of disk, the impeller disk is compressor disc or the turbine disk, and the inner wall of the ring bodies is equipped with an annular support wall,
It is characterized in that,
The annular support wall and the axial position of the central tube are at least substantially identical, and are uniformly arranged in the circumferential direction therebetween
Multiple water conservancy diversion prismatic blades, the space between adjacent two water conservancy diversion prismatic blade form drainback passage, and the lubricating oil in the bearing bore is logical
Each drainback passage for crossing the vane type wheel disc flows into the lubricant reservoir, the cross section of each guide vane be it is wing,
The selection of aerofoil profile parameter is not so that by the flowing in each drainback passage apparent segregation phenomenon is occurring for incoming flow.
2. the vane type wheeling disk structure according to the claims, which is characterized in that the central tube passes through card slot and spiral shell
Nail is fixed on the central axis, and each water conservancy diversion prismatic blade and the junction of the annular support wall and central tube are respectively provided with
There is knuckle.
3. the vane type wheeling disk structure according to the claims, which is characterized in that the annular support wall and the ring
The junction of wall is provided with knuckle in shape body.
4. the vane type wheeling disk structure according to the claims, which is characterized in that the inner wall of the ring bodies is described
Annular support wall is divided into front half section and second half section, and the second half section has the tilt angle expanded outwardly.Preferably, described to incline
Rake angle is 5~15 °.
5. the vane type wheeling disk structure according to the claims, which is characterized in that the quantity root of the water conservancy diversion prismatic blade
According to the design pressure difference and lubricants capacity determination between the bearing bore and lubricant reservoir.
6. the vane type wheeling disk structure according to the claims, which is characterized in that the return flow line can use part
Intake method adjusts the relationship of flow and stability.
7. the vane type wheeling disk structure according to the claims, which is characterized in that before the aerofoil profile of the water conservancy diversion prismatic blade
Edge uses thickness appropriate and stagger angle, and blade trailing edge uses small as far as possible thickness and exit installation angle appropriate, to protect
Card blade strength requires and avoids trailing edge flow separation.
8. the vane type wheeling disk structure according to the claims, which is characterized in that an annular is arranged in the front half section
Keep off oily boss, the oily boss of the gear with before obturage ring and radially contact with, be 3~8mm away from the axial distance for preceding obturaging ring tail end.
9. a kind of with vane type wheeling disk structure gas turbine lubricant passage way system described in any of the above-described claim.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811472856.3A CN109707515B (en) | 2018-12-04 | 2018-12-04 | Impeller type wheel disc structure for gas turbine lubricating oil way system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811472856.3A CN109707515B (en) | 2018-12-04 | 2018-12-04 | Impeller type wheel disc structure for gas turbine lubricating oil way system |
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| CN109707515A true CN109707515A (en) | 2019-05-03 |
| CN109707515B CN109707515B (en) | 2020-04-21 |
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| CN201811472856.3A Active CN109707515B (en) | 2018-12-04 | 2018-12-04 | Impeller type wheel disc structure for gas turbine lubricating oil way system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN112943901A (en) * | 2021-02-05 | 2021-06-11 | 中国航发沈阳发动机研究所 | Gear transmission structure |
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| 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 |
| CN112943901A (en) * | 2021-02-05 | 2021-06-11 | 中国航发沈阳发动机研究所 | Gear transmission structure |
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| Publication number | Publication date |
|---|---|
| CN109707515B (en) | 2020-04-21 |
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