CN105275499B - A kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging - Google Patents
A kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging Download PDFInfo
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- CN105275499B CN105275499B CN201510360011.5A CN201510360011A CN105275499B CN 105275499 B CN105275499 B CN 105275499B CN 201510360011 A CN201510360011 A CN 201510360011A CN 105275499 B CN105275499 B CN 105275499B
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- turbine disk
- air intake
- double disc
- disc turbine
- effect
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Abstract
The invention discloses a kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging, be made up of inlet channel (1), centrifugeblade (4) and rotary lip seal structure (3).Inlet channel (1) is in the cavity in rotary lip seal structure (3)；Centrifugeblade (4) is positioned in inlet channel (1), and cooling gas is centrifuged supercharging, intensification；Rotary lip seal structure (3) is positioned at the double disc turbine disk (9) core, axially obturages cooling gas.Double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging of the present invention, on the premise of alleviating wheel disc quality, it is possible to makes full use of cold air and realizes efficient dish chamber fluid interchange effect, wheel disc active thermal Stress Control and cold air and obturage.This structure can be effectively improved the level that utilizes cold air, and structure design, processing are simply, it is easy to realizes in actual type.
Description
Technical field
The invention belongs to aero-engine high-pressure turbine dish cooling technology field, particularly relate to one and have centrifugal
Supercharging and double disc turbine disk core air intake structures of effect of obturaging.
Background technology
Along with the development of engine technology, thrust-weight ratio constantly increases, even to this day, and high-pressure turbine dish
Dish edge temperature up to 700 DEG C, distance high-temperature combustion gas core temperature farther out generally also at about 400 DEG C, work
Being up to about 16000r/min as rotating speed, the working environment which results in high-pressure turbine dish is more and more severe, passes
The single disc turbine disk of system has been difficult to meet the design requirement of advanced big thrust loading electromotor, seriously limits boat
The further development of empty electromotor.
Double disc turbine disks be high Property in America propeller for turboprop machine technology (IHPTET) plan under, under
A generation high thrust-weight ratio fanjet high-pressure turbine dish design, propose lightweight, high cooling efficiency novel
Turbine disc structure designing technique.Compared with conventional turbine dish, this calculated pair of disc turbine disk employing dish chamber
Cooling structure, reduces each plate convergence axial width by hollowing out in the middle part of disc, alleviate quality, optimizes power transmission
Path；By increase dish chamber heat exchange area improve cooling effectiveness, reduce turbine disk dish body bulk temperature and
Temperature difference.
Patent US1999/005961287A proposes a kind of double disc turbines distinguishing the most single disc turbine disk
Dish.This turbine disk is welded by two symmetry half dishes, wheel disc intermediate formation dish cavity configuration, and two spokes
Pad is added between the core of plate.Cold air, by the perforate entrance dish chamber at core, on the one hand alleviates wheel disc weight
Amount, additionally increases dish chamber fluid interchange area.
Patent US2005/0025627A1 proposes another kind does not has double disc turbine disks of pad between core to tie
Structure.This turbine disk for preventing two disc under high rotating speed from contacting due to axial deformation at core, its hub
Size is bigger.
Patent US2000/6267553B1 proposes a kind of double disc wheel discs applied on high-pressure compressor.This
It is passed through cold air between two disc of wheel disc and preferably can cool down wheel disc thus the thermal stress water that controls on wheel disc
Flat.
Patent CN2014/104196572A proposes a kind of double disc turbine disks with dish chamber diversion rib plate,
Being provided with some diversion rib plates on two disc of double disc turbine disks, turbine disk Pan Yuanchu is circumferentially the most all
Cloth dish edge cold air path, by dish edge cold air path, from double disc turbine disk dish chambeies, entrance cools down blade to cold air.
It is contemplated that disc strength requirement, double disc turbine disks can not punch on disc, and it cools down air-flow
Can only be by core radially into dish chamber.Cooling air-flow is from the axial bleed of high-pressure compressor, core footpath
Needing to turn back cold air to intake method, this inevitably results in the loss of cold air flow and pressure, cold air flow
Loss can reduce the heat transfer effect of the turbine disk, increases amount of air entrainment and engine efficiency can be caused to reduce, and cold air
The pressure loss can reduce the heat transfer effect of wheel disc and blade, and the situation of pressure of compressed air wretched insufficiency may cause
Main flow combustion gas suck-back thus burn blade and wheel disc.It addition, turbine disk Pan Yuanchu close to combustion gas, temperature high,
Core radial air inlet is to flow into again through dish chamber cooling plate convergence and dish edge from the core that temperature is relatively low, if do not improved
Cold air quality, strengthens disc and the cooling effect of dish edge, will very likely result the radial temperature difference that wheel disc is bigger.
It is, therefore, necessary to reasonably design the core air intake structure of double disc turbine disk, comprehensively utilize " centrifugal compressor
Principle ", " pumping effect " and the Cooling Design method such as exemplary disc cavity configuration, active thermal Stress Control,
Wheel disc cold air could be effectively compensated for and obturage and could improve wheel disc fluid interchange effect and fall further
Low cooling tolerance.
Summary of the invention
Instant invention overcomes the deficiencies in the prior art, it is provided that a kind of for the double disc turbine disk of aero-engine
Core air intake structure, compared with the conventional turbine dish type of cooling, it can to cold air produce axial seal and from
Heart supercharging, the effect of intensification, cold air axial seal ensure that the cold air entrance dish chamber of q.s；Promote cold
Atmospheric pressure can improve dish chamber fluid interchange efficiency and improve the cold air quality entering turbo blade；Promote chill temperature
Degree can play the effect of active thermal Stress Control, makes core temperature be unlikely to the lowest, reduces wheel disc radially
The temperature difference, thus reduce wheel disc thermal stress distribution.
In view of the problems referred to above of prior art, according to an aspect disclosed by the invention, the present invention use with
Lower technical scheme:
A kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging, by inlet channel
1, centrifugeblade 4 and rotary lip seal structure 3 form.Inlet channel 1 is in rotary lip seal structure 3
In cavity, cooling gas flows out air intake structure venthole 8 through cold air import 2 through inlet channel 1 and enters double
The disc turbine disk 9 dish chamber；Centrifugeblade 4 uses conventional centrifugal Compressor airfoil, is positioned in inlet channel 1, right
Cooling gas is centrifuged supercharging, intensification, and is used for supporting inlet channel 1 and rotary lip seal structure 3；
Rotary lip seal structure 3 is positioned at the double disc turbine disk 9 core, and connects the left disc 11 of double disc turbine disk 9
With right disc 12, cooling gas is axially obturaged, it is ensured that enough cooling gas flows enter inlet channel 1.
Inlet channel 1, centrifugeblade 4 and rotary lip seal structure 3, by hot investment casting one-shot forming, pass through interference
Coordinate and be arranged at the double disc turbine disk 9 core.
A kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging of the present invention, by
High temperature alloy precision casting forms, and the core along double disc turbine disks 9 is annular.
The angle that the leading edge of rotary lip seal structure 3 and engine shaft are constituted is leading edge angle 5, rotation
The minimum range turning lip seal structure 3 and engine shaft is gap 6, giving vent to anger of rotary lip seal structure 3
The angle that limit and engine shaft are constituted is corner degree 7 of obturaging, by leading edge angle 5, gap 6, limit of obturaging
The air conditioning quantity adjusting control entrance dish chamber of 7 three parameters of angle.
It is disposed with the centrifugeblade 4 of 11-33 employing centrifugal compressor blade profile in inlet channel 1, plays centrifugal increasing
Pressure effect and support whole air intake structure.
A kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging of the present invention, tool
There is a following features:
Use the core air inlet of double disc turbine disks of inlet channel, centrifugeblade, rotary lip seal structure
Structure, has no in existing patent documentation and mentions.
The air intake structure of the present invention is arranged at the core of double disc turbine disk by interference fit, cold air warp
Cross inlet channel enter wheel disc dish chamber, axial cold air can be played on the way centrifugal supercharging, the effect of intensification and
The effect of axially obturaging of cold air.
Cold air heats up at core and can play the purpose of core Thermal Stress Control, reduces wheel disc radial temperature difference；
The centrifugal supercharging of cold air can change air-flow trend, and improves dish chamber cooling effectiveness and lifting dish edge exit is cold
The quality of gas, more preferable cooling turbine bucket；Cold air is axially obturaged and be can guarantee that the air conditioning quantity entrance dish by enough
Chamber.
In view of the physical dimension of the double disc turbine disk of the present invention, this air intake structure maximum radius 61.7mm,
Minor radius 31.7mm, radical length is 30mm, Breadth Maximum 45mm, upper end outlet width 11mm, gap 3mm.
For the various sizes of pair of disc turbine disk, for realizing identical function, its air intake structure size can suitably change,
But its topological form is constant.
Air intake structure has 11-33 centrifugeblade, is to make according to centrifugal compressor blade profile, it is possible to by cold air
Centrifugal supercharging, intensification.
Use existing high-temperature alloy material (such as GH4169), requirement can be met.
Compared with the cooling structure of conventional turbine dish and the type of cooling, the present invention is applicable to more advanced double disc
The cooling structure of the turbine disk and the type of cooling, on the premise of alleviating wheel disc quality, it is possible to make full use of cold air
Realize efficient dish chamber fluid interchange effect, wheel disc active thermal Stress Control and cold air to obturage.This structure designs
Level that cold air is utilized can be effectively improved, and structure design, processing are simply, it is easy in actual type
Realize.
Accompanying drawing explanation
Fig. 1 shows the core air intake structure schematic diagram of double disc turbine disks of a sector.
Fig. 2 shows the core air intake structure two dimension view without centrifugeblade.
Fig. 3 shows core air intake structure 3-D view.
Drawing reference numeral illustrates:
1-inlet channel, 2-cold air import, 3-rotary lip seal structure, 4-centrifugeblade, 5-leading edge
Angle, 6-gap, 7-obturages corner degree, 8-air intake structure venthole, the double disc turbine disk of 9-, 10-dish edge,
The left disc of 11-, the right disc of 12-.
Detailed description of the invention
Below in conjunction with embodiment, the present invention is described in further detail, but embodiments of the present invention do not limit
In this.
A kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging of the present invention, by
Inlet channel 1, centrifugeblade 4 and rotary lip seal structure 3 form.Inlet channel 1 is in rotary lip
Cavity in seal structure 3, cooling gas flows out air intake structure through cold air import 2 through inlet channel 1 gives vent to anger
Hole 8 enters the double disc turbine disk 9 dish chamber；Centrifugeblade 4 uses conventional centrifugal Compressor airfoil, is positioned at air inlet and leads to
In road 1, cooling gas is centrifuged supercharging, intensification, and is used for supporting inlet channel 1 and rotary lip envelope
Tight structure 3；Rotary lip seal structure 3 is positioned at the double disc turbine disk 9 core, and connects double disc turbine disk 9
Left disc 11 and right disc 12, to cooling gas axially obturage, it is ensured that enough cooling gas flow entrance
Inlet channel 1.Inlet channel 1, centrifugeblade 4 are once become by hot investment casting with rotary lip seal structure 3
Type processes, and is arranged at the double disc turbine disk 9 core by interference fit.
As shown in Figure 1, Figure 2, Figure 3 shows, the detailed description of the invention of the present invention is as follows:
The present invention is a kind of air intake structure that can be effectively improved double disc turbine disk cooling effect, and it is by air inlet
Passage, centrifugeblade form with rotary lip seal structure: inlet channel becomes toroidal, the inside to be disposed with
17 centrifugeblades, by adjusting leading edge angle, obturage corner degree and gap realizes axially obturaging of cold air.
Total passes through hot investment casting one-shot forming.
Fig. 1 is the core air intake structure schematic diagram of double disc turbine disks of a sector, and centrifugeblade uses centrifugal
Compressor airfoil designs, and air intake structure is arranged at double disc turbine disk core by interference fit.
Fig. 2 is the core air intake structure two dimension view without centrifugeblade, air intake structure maximum radius 61.7mm,
Least radius 31.7mm, radical length is 30mm, Breadth Maximum 45mm, upper end outlet width 11mm, gap
3mm。
Fig. 3 is core air intake structure 3-D view, comprises 17 centrifugeblades, 17 air intake structure ventholes.
The air intake structure of the present invention, have employed that " centrifugal compressor principle " and " pumping effect " combine
Thinking, makes full use of the centrifugal supercharging of centrifugal compressor and pumping is obturaged effect, makes the cooling capacity of cold air obtain
To playing, and play the purpose of active thermal Stress Control to a certain extent.This structure designs, processing is simple,
It is prone in actual type realize.
Claims (4)
1. there are a double disc turbine disk core air intake structures for centrifugal supercharging and effect of obturaging, air inlet lead to
Road (1), centrifugeblade (4) and rotary lip seal structure (3) composition: inlet channel (1) is position
Cavity in rotary lip seal structure (3), cooling gas leads to through air inlet through cold air import (2)
Road (1) flows out air intake structure venthole (8) and enters the double disc turbine disk (9) dish chamber；Centrifugeblade (4)
Use conventional centrifugal Compressor airfoil, be positioned in inlet channel (1), to cooling gas be centrifuged supercharging,
Heat up, and be used for supporting inlet channel (1) and rotary lip seal structure (3)；Rotary lip is obturaged knot
Structure (3) is positioned at the double disc turbine disk (9) core, and connects the left disc (11) of double disc turbine disk (9)
With right disc (12), cooling gas is axially obturaged, it is ensured that enough cooling gas flow entrance air inlets are led to
Road (1)；Inlet channel (1), centrifugeblade (4) and rotary lip seal structure (3) are by precision
Casting one-shot forming, is arranged at the double disc turbine disk (9) core by interference fit.
A kind of double disc turbine disk dishes with centrifugal supercharging and effect of obturaging the most according to claim 1
Heart air intake structure, it is characterised in that: air intake structure is formed by high temperature alloy precision casting one-shot forming, along double
The core of the disc turbine disk (9) is annular.
A kind of double disc turbine disk dishes with centrifugal supercharging and effect of obturaging the most according to claim 1
Heart air intake structure, it is characterised in that: the leading edge of rotary lip seal structure (3) and engine shaft are constituted
Angle be leading edge angle (5), rotary lip seal structure (3) and the minimum range of engine shaft
The angle constituted for gap (6), the trailing edge of rotary lip seal structure (3) and engine shaft is envelope
Tight corner degree (7), by leading edge angle (5), gap (6), corner degree (7) three ginseng of obturaging
The air conditioning quantity adjusting control entrance dish chamber of number.
A kind of double disc turbine disk dishes with centrifugal supercharging and effect of obturaging the most according to claim 1
Heart air intake structure, it is characterised in that: it is disposed with 11-33 employing centrifugal compressor leaf in inlet channel (1)
The centrifugeblade (4) of type, plays the effect of centrifugal supercharging and supports whole air intake structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510360011.5A CN105275499B (en) | 2015-06-26 | 2015-06-26 | A kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510360011.5A CN105275499B (en) | 2015-06-26 | 2015-06-26 | A kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging |
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| Publication Number | Publication Date |
|---|---|
| CN105275499A CN105275499A (en) | 2016-01-27 |
| CN105275499B true CN105275499B (en) | 2016-11-30 |
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| CN201510360011.5A Expired - Fee Related CN105275499B (en) | 2015-06-26 | 2015-06-26 | A kind of double disc turbine disk core air intake structures with centrifugal supercharging and effect of obturaging |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014485B (en) * | 2016-07-01 | 2017-09-12 | 中航空天发动机研究院有限公司 | A kind of water conservancy diversion cooling structure for being applied to double disc turbine disk disk chambers |
| CN106089310B (en) * | 2016-07-01 | 2017-08-29 | 中航空天发动机研究院有限公司 | A kind of double disc turbine disks of the fiber reinforcement for improving disc bearing capacity |
| CN106837431A (en) * | 2016-12-26 | 2017-06-13 | 北京航空航天大学 | A kind of method for improving aero gas turbine engine transient process turbine blade air film cooling air-flow quality |
| CN114135340A (en) * | 2021-12-03 | 2022-03-04 | 西北工业大学太仓长三角研究院 | Binary channels refrigerated turbine bladed disk |
| CN117722235B (en) * | 2024-02-18 | 2024-05-17 | 中国航发四川燃气涡轮研究院 | Double-radial-plate turbine disc |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB617472A (en) * | 1946-10-02 | 1949-02-07 | Adrian Albert Lombard | Improvements in or relating to gas-turbine-engines |
| US5961287A (en) * | 1997-09-25 | 1999-10-05 | United Technologies Corporation | Twin-web rotor disk |
| US6267553B1 (en) * | 1999-06-01 | 2001-07-31 | Joseph C. Burge | Gas turbine compressor spool with structural and thermal upgrades |
| US7241111B2 (en) * | 2003-07-28 | 2007-07-10 | United Technologies Corporation | Contoured disk bore |
| US7665965B1 (en) * | 2007-01-17 | 2010-02-23 | Florida Turbine Technologies, Inc. | Turbine rotor disk with dirt particle separator |
| EP2025867A1 (en) * | 2007-08-10 | 2009-02-18 | Siemens Aktiengesellschaft | Rotor for an axial flow engine |
| JP4939461B2 (en) * | 2008-02-27 | 2012-05-23 | 三菱重工業株式会社 | Turbine disc and gas turbine |
| US8348599B2 (en) * | 2010-03-26 | 2013-01-08 | General Electric Company | Turbine rotor wheel |
| US8944767B2 (en) * | 2012-01-17 | 2015-02-03 | Hamilton Sundstrand Corporation | Fuel system centrifugal boost pump impeller |
| 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 |
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