CN103511003B - Control system - Google Patents
Control system Download PDFInfo
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- CN103511003B CN103511003B CN201210220517.2A CN201210220517A CN103511003B CN 103511003 B CN103511003 B CN 103511003B CN 201210220517 A CN201210220517 A CN 201210220517A CN 103511003 B CN103511003 B CN 103511003B
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- control system
- blade
- housing
- driving mechanism
- baffle plate
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Abstract
A kind of control system, it is in gas turbine engine, and control system comprises: axle, and it longitudinally extends; Blade, it is arranged on axle, and radially stretches out and form blade tip; Housing, it surrounds blade; Driving mechanism, it is fixed on housing; Baffle plate, it can be drivingly coupled to driving mechanism, and limits gap with the blade tip of blade; Sensor, its be arranged in blade, housing, driving mechanism and baffle plate one of them on for detector gap; Controller, itself and sensor and driving mechanism couple and the response sensor gap that detects regulates gap to control driving mechanism to the driving of baffle plate.
Description
Technical field
The present invention relates to control system, particularly relate to the control system controlling turbine blade-tip gap.
Background technique
Motor is operated in different gas flow temperature states along with thrust adjustment and external air temperature change, and because rotor is different with the rates of thermal expansion of casing, the gap of blade tip and casing also changes with engine behavior.Tip clearance has material impact to the efficiency of turbine and the fuel consumption rate of motor.Tip clearance increases, and working fluid will increase from the leakage rate of tip clearance, increases leakage rate and can reduce turbine efficiency and the fuel consumption rate of motor is increased.The research of associated mechanisms finds: turbine blade-tip gap often increases 1% of length of blade, and efficiency reduces by 1.5%; Efficiency often reduces by 1%, and oil consumption rate about increases by 2%.In addition, the deterioration of tip clearance also can cause the generation of surge, threatens the Security of motor.
In order to prevent the unfavorable effect brought because tip clearance changes, need to control the tip clearance of rotor part.The controlling method of turbine blade-tip gap can be divided into two kinds: active clearance controls and passive gap control.The Large Civil Aircraft motor of current international mainstream all have employed active clearance control technique.Such as, CFM56 motor adopts high-pressure turbine active clearance to control.This system uses two strands from the air-flow of high-pressure compressor, by the proportions of ingredients of active clearance control valve controlled cooling model air quantity and two kinds of air-flows.According to the requirement of regulating radial clearance, the cooling-air attracting different temperatures under different working staties cools casing or heats, and ensures in cruising, have less tip clearance.
Tip clearance measuring transducer is one of key technology of active clearance control, all it can be used as research emphasis both at home and abroad.Tip clearance measuring transducer relatively more conventional at present can be divided into microwave type, condenser type and optical fiber type etc., US National Aeronautics and Space Administration's (NationalAeronauticsandSpaceAdministration is called for short NASA) adopts microwave type sensor to carry out tip clearance and measures test; Group of Aérospatiale Matra uses capacitive transducer to measure tip clearance on its TP400 motor; The high frequency carrier electric capacity amplitude modulation tip clearance of China measures sensing device initial industrialization production.
Current application active clearance on the engine controls substantially to adopt to cool casing or heat and controls its swell increment.But due to casing expansion and shrink and need certain response time, namely this method response is slower.
In order to overcome the shortcoming of above-mentioned low-response, the present invention proposes a kind of mechanical type active clearance control system of fast and reliable.
Summary of the invention
The present invention proposes a kind of type aeroengine turbine blade tip gap active control system, turbine efficiency can be improved.This system critical piece is mechanical type actuator and sensor, and the main feature of this system is: adopt sensor measure tip clearance parameter in real time and go out tip clearance by airborne computer computational analysis; Mechanical type actuator is adopted to adjust tip clearance according to the real-time measuring data of sensor.
Sensor in this control system has the advantage of real-time measurement, response fast; Mechanical type actuator has reliable, quick response, is easy to the advantage of maintenance.
Particularly, the invention discloses a kind of for the control system in gas turbine engine, described control system comprises:
Axle, it longitudinally extends;
Blade, it is installed on the shaft, and radially stretches out and form blade tip;
Housing, it surrounds described blade;
Baffle plate, the blade tip of itself and described blade limits gap;
Driving mechanism, it is fixing on the housing, and described driving mechanism connects and drives described baffle plate to radially move;
Sensor, its be arranged in described blade, housing, driving mechanism and baffle plate one of them on for detecting described gap;
Controller, itself and described sensor and described driving mechanism couple and respond gap that described sensor detects and regulate described gap to control described driving mechanism to the driving of described baffle plate.
Preferably, described baffle plate is one piece of circular plate washer.Selectively, described baffle plate is polylith curved baffle, and described polylith curved baffle forms circle in the circumferential.
Particularly, the corresponding described curved baffle of the number of described driving mechanism number and arrange.
Particularly, described sensor is arranged between two curved baffles adjacent one another are.
Particularly, the rotating component that described driving mechanism comprises power source, driven by described power source and the leading screw be at one end threaded with described rotating component, wherein, described rotating component is pivotally connected on described housing, and the other end of described leading screw is connected to described baffle plate.
Preferably, the link with described housing and described rotating component sliding friction is also furnished with between described rotating component and described housing.
More preferably, described link is ball.
Preferably, the link rubbed with described housing and described barrier slides is also furnished with between described housing and described baffle plate.
More preferably, described link is roller.
Particularly, described controller is airborne computer.
Particularly, described blade is compressor stator vanes.
Selectively, described blade is turbine rotor blade.
Control system of the present invention can respond and reliable and stable fast, this system is applied to active clearance and controls, can effectively reduce turbine blade-tip gap, improve turbine efficiency.
Accompanying drawing explanation
In order to explain the present invention, its illustrative embodiments will be described with reference to the drawings hereinafter, in accompanying drawing:
Fig. 1 schematically shows the schematic diagram of the cross section of the control system when baffle plate is in the first state;
Fig. 2 schematically shows the schematic diagram of the cross section of the control system when baffle plate is in the second state;
Fig. 3 schematically shows the partial enlarged drawing of control system;
Fig. 4 schematically shows control system schematic diagram circumferentially;
Fig. 5 schematically shows the skeleton diagram of control system.
Wherein, in figure, 1 represents housing, and 2 represent blade, and 3 represent baffle plate, and 4 represent leading screw, and 5 represent rotating component, and 6 represent ball, and 7 represent roller, and 8 represent sensor.
Similar features in different figure is indicated by similar reference character.
Embodiment
As Figure 1-Figure 4, a control system for gas turbine engine, it to comprise in the axle of longitudinal extension, the blade 2 be arranged on axle, circumference around this blade 2 to surround the toroidal shell 1 of blade 2, the driving mechanism 9 be fixedly mounted on housing 1, the baffle plate 3 that can be connected to driving mechanism 9 with driving and sensor 8 and controller 10.Wherein, blade 2 has blade root and blade tip, and blade root is combined by the tongue-and-groove on tenon portion and axle thus makes blade 2 be fixed on axle, is limited with gap between blade tip and the baffle plate 3 being connected on housing 1.The two ends on the top of housing 1 are outward extended with mounting flange respectively in the circumferential, and for installing following rotating component 5, the two ends of the bottom of housing 1 have extended internally guide rib respectively diametrically, for guide baffle plate 3 movement diametrically.Those skilled in the art should be appreciated that the concrete structure of mounting flange and guide rib is not determinate, as long as baffle plate can be arranged on housing and can other structures of movement to be diametrically all fine.For example, substituting as guide rib, can be provided with groove by the bottom of housing, accordingly, baffle plate is provided with the projection be fitted to slidably in groove simultaneously.
As shown in Figure 4, in preferrred embodiment of the present invention, this baffle plate 3 is made up of polylith curved baffle, and these curved baffles form circle in the circumferential.Accordingly, the number of this driving mechanism 9 is equal with the number of these curved baffles 3, that is, be six, by this, can drive in man-to-man mode to every block curved baffle 3.Sensor 8 is arranged between two pieces of curved baffles 3 adjacent one another are.The benefit that each curved baffle 3 carries out driving separately is, can circumferentially ensures that when disalignment appears in blade 2 gap width between each curved baffle 3 and the blade tip of blade 2 is consistent.Those of ordinary skill in the art should be appreciated that the number of this driving mechanism can be less than the number of curved baffle or be only one, can drive like this with a driving mechanism to several curved baffle or whole curved baffle.
According to preferrred embodiment of the present invention, driving mechanism comprises power source (not shown), rotating component 5 and leading screw 4, wherein power source can be motor, its power can come from the generator of aircraft, the mounting flange that rotating component 5 is rotatably installed to housing 1 is rotated by the driving of power source, rotating component 5 also has tapped through hole, and on the tapped through hole that one end of leading screw 4 is rotatably connected on rotating component 5, the other end is fixedly attached on curved baffle 3.The link of such as ball 6 can be provided with between rotating component 5 and housing 1, like this, when rotating component 5 rotates relative to housing 1, this link respectively with rotating component 5, housing 1 sliding friction.Slide more swimmingly to make the relative housing 1 of curved baffle 3, the link of multiple such as roller 7 can be set between housing 1 and curved baffle 3, like this, when curved baffle 3 moves diametrically relative to housing 1, these links respectively with housing 1 and curved baffle 3 sliding friction.
In preferrred embodiment of the present invention, sensor 8 is arranged on housing 1.Together with controller 10, sensor 8 and driving mechanism 9 are coupled in the mode of electrical connection, the sensed data of sensor 8 passes to controller 10, and controller 10 controls driving mechanism 9 by these sensed data again.Wherein, controller 10 is airborne computer.Those skilled in the art should be appreciated that the mounted position of sensor can be arbitrary, that is, can be arranged on blade, also can be arranged on housing, can also be arranged on driving mechanism or baffle plate, as long as can meet mounting design requirement.
Composition graphs 5, when gas turbine engine works, the gap between every block curved baffle 3 and housing 1 monitored all in real time by each sensor 8, and this gap width as Δ 1 sends to controller 10, controller 10 working state current according to motor calculates the gap width Δ 2 allowed between every block curved baffle 3 and housing 1, and Δ 1 and Δ 2 are compared, if Δ 1 is greater than Δ 2, then sends instruction to driving mechanism 9 and drive curved baffle 3 to be radially moved into and the position of housing 1 at a distance of Δ 2 to make driving mechanism 9.When above-mentioned driving mechanism 9 start, rotating component 5 rotates relative to leading screw 4, meanwhile, curved baffle 3 away from housing 1 mounting flange thus the blade tip of curved baffle 3 closer to blade 2 is diminished to make gap width.As for the control algorithm method of controller 10, also have a lot, such as, can gap width between prestor type motor (comprises Turbine Blade Temperature Field, case temperature, working time, flying height etc.) under each working state in controller curved baffle and blade tip, then the real time data sent according to sensor is compared, and then regulates.Because concrete controlling method does not belong to emphasis of the present invention, therefore do not repeat them here.
This control system can be the control system controlled for turbine blade tip clearance, and particularly, blade can be turbine rotor blade, and housing can be turbine casing.Selectively, this control system can be the control system controlled for the tip clearance of compressor stator vanes, and particularly, blade can be compressor stator vanes, and housing can be compressor casing.
The present invention is limited to the illustrative embodiments presented in the specification and illustrated in the drawings never in any form.All combinations of the mode of execution (part) illustrated and describe are interpreted as clearly to be incorporated within this specification and to be interpreted as clearly and fall within the scope of the present invention.And in the scope of the present invention that such as claims are summarized, a lot of distortion is possible.In addition, any reference mark in claims should be configured to limit the scope of the invention.
Claims (10)
1. a control system, it is in gas turbine engine, and described control system comprises:
Axle, it longitudinally extends;
Blade, it is installed on the shaft, and radially stretches out and form blade tip;
Housing, it surrounds described blade;
Driving mechanism, it is fixing on the housing;
Baffle plate, it can be drivingly coupled to described driving mechanism, and limits gap with the blade tip of described blade;
Sensor, its be arranged in described blade, housing, driving mechanism and baffle plate one of them on for detecting described gap;
Controller, itself and described sensor and described driving mechanism couple and respond gap that described sensor detects and regulate described gap to control described driving mechanism to the driving of described baffle plate;
Wherein, the rotating component that described driving mechanism comprises power source, driven by described power source and the leading screw be at one end threaded with described rotating component, wherein, described rotating component is pivotally connected on described housing, and the other end of described leading screw is connected to described baffle plate;
Wherein, the link rubbed with described housing and described barrier slides is also furnished with between described housing and described baffle plate;
Wherein, described link is roller.
2. control system according to claim 1, is characterized in that, described baffle plate is one piece of circular plate washer.
3. control system according to claim 1, is characterized in that, described baffle plate is polylith curved baffle, and described polylith curved baffle forms circle in the circumferential.
4. control system according to claim 3, is characterized in that, the number of the corresponding described curved baffle of the number of described driving mechanism and arranging.
5. control system according to claim 3, is characterized in that, described sensor is arranged between two curved baffles adjacent one another are.
6. control system according to claim 1, is characterized in that, is also furnished with the link with described housing and described rotating component sliding friction between described rotating component and described housing.
7. control system according to claim 6, is characterized in that, described link is ball.
8. the control system according to any one of claim 1-7, is characterized in that, described controller is airborne computer.
9. the control system according to any one of claim 1-7, is characterized in that, described blade is compressor stator vanes.
10. the control system according to any one of claim 1-7, is characterized in that, described blade is turbine rotor blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210220517.2A CN103511003B (en) | 2012-06-28 | 2012-06-28 | Control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210220517.2A CN103511003B (en) | 2012-06-28 | 2012-06-28 | Control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103511003A CN103511003A (en) | 2014-01-15 |
| CN103511003B true CN103511003B (en) | 2015-12-16 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210220517.2A Active CN103511003B (en) | 2012-06-28 | 2012-06-28 | Control system |
Country Status (1)
| Country | Link |
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| CN (1) | CN103511003B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111963470A (en) * | 2020-08-07 | 2020-11-20 | 中国北方发动机研究所(天津) | Turbocharger compressor clearance control device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2099515A (en) * | 1981-05-29 | 1982-12-08 | Rolls Royce | Shroud clearance control on a gas turbine engine |
| US4878821A (en) * | 1987-02-11 | 1989-11-07 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Detachable anti-rupture ring for the housing of a turbo power plant |
| US5054997A (en) * | 1989-11-22 | 1991-10-08 | General Electric Company | Blade tip clearance control apparatus using bellcrank mechanism |
| US5096375A (en) * | 1989-09-08 | 1992-03-17 | General Electric Company | Radial adjustment mechanism for blade tip clearance control apparatus |
| CN101660431A (en) * | 2008-08-29 | 2010-03-03 | 通用电气公司 | System and method for adjusting clearance in a gas turbine |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10060740A1 (en) * | 2000-12-07 | 2002-06-13 | Alstom Switzerland Ltd | Device for setting gap dimensions for a turbomachine |
| GB0513654D0 (en) * | 2005-07-02 | 2005-08-10 | Rolls Royce Plc | Variable displacement turbine liner |
| US8186945B2 (en) * | 2009-05-26 | 2012-05-29 | General Electric Company | System and method for clearance control |
-
2012
- 2012-06-28 CN CN201210220517.2A patent/CN103511003B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2099515A (en) * | 1981-05-29 | 1982-12-08 | Rolls Royce | Shroud clearance control on a gas turbine engine |
| US4878821A (en) * | 1987-02-11 | 1989-11-07 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Detachable anti-rupture ring for the housing of a turbo power plant |
| US5096375A (en) * | 1989-09-08 | 1992-03-17 | General Electric Company | Radial adjustment mechanism for blade tip clearance control apparatus |
| US5054997A (en) * | 1989-11-22 | 1991-10-08 | General Electric Company | Blade tip clearance control apparatus using bellcrank mechanism |
| CN101660431A (en) * | 2008-08-29 | 2010-03-03 | 通用电气公司 | System and method for adjusting clearance in a gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103511003A (en) | 2014-01-15 |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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