CN101050712A - Positive control for aviation engine turbine blade-tip gap - Google Patents
Positive control for aviation engine turbine blade-tip gap Download PDFInfo
- Publication number
- CN101050712A CN101050712A CN 200710107216 CN200710107216A CN101050712A CN 101050712 A CN101050712 A CN 101050712A CN 200710107216 CN200710107216 CN 200710107216 CN 200710107216 A CN200710107216 A CN 200710107216A CN 101050712 A CN101050712 A CN 101050712A
- Authority
- CN
- China
- Prior art keywords
- gap
- turbine blade
- tip
- control
- tip clearance
- 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.)
- Pending
Links
Abstract
The present invention provides a new-type aeroengine turbine blade tip gap active control system. It is characterized by that said system can be combined with characteristics of open gap control and closed gap control system. The airborne computer can be used fro collecting the signals of existent sensors (including rotating speed sensor, temperature sensor and pressure sensor, etc.) on the engine and real-time calculating turbine blade tip gap value by using advanced blade tip gap analysis program. When the blade tip gap control unit is used for making gap control, the displacement sensor can be used for back feeding the gap control quantity of the execution mechanism to the control unit.
Description
One, technical field
The ACTIVE CONTROL of tip clearance can improve the efficient of aeroengine significantly, reduces fuel consumption rate.Aeroengine then needs the fast active control system (FACC) of tip clearance when improving Economy, and guarantees the requirement of Security.
Two, background technique
2.1 research background and meaning
The aeroengine tip clearance typically refers to the radial clearance between axial-flow engine rotor blade blade tip and the machine lock.Tip clearance all has great influence to the efficient of aeroengine fuel consumption rate, stability and turbine and gas compressor, and especially the influence to back what and the high-pressure turbine of high-pressure compressor is then bigger.Therefore, all attach great importance to for the research of aeroengine interlobar fissure problem both at home and abroad.
The blade tip clearance of high-pressure turbine has very big influence to the performance of motor, and for Economy and the reliability that improves modern aeroengine, the research institution of lot of domestic and international has all successively carried out the research of blade tip clearance active control technology aspect.This is because advanced turbine blade tip clearance active control technology can reduce fuel consumption rate (SFC) and delivery temperature (EGT) significantly; When having improved engine efficiency, also the aircraft flight radius of Zeng Daing and the life-span of motor.Therefore the research of further carrying out high-pressure turbine blade tip clearance active control technology aspect has the practical project meaning.
According to the U.S. GE company CF6-50 motor be the analysis showed that the loss of the oil consumption rate that its gas compressor, turbine blade tip clearance cause accounts for 67% of total losses.The high-pressure turbine blade tip clearance increases by 0.001 inch, and SFC will increase about 0.1% and EGT will increase by 1 ℃.The SFC of ordnance engine, EGT are subjected to the influence of turbine blade tip clearance more remarkable, and this is because for large commercial airplane engine (high bypass ratio), and the rotating speed and the turbine inlet temperature of ordnance engine (low bypass ratio) are all higher.Turbine blade tip clearance and the every increase by 0.01 of the ratio of leaf height, it is about 0.8～1.2% to cause that turbine efficiency reduces, efficient reduce by 1% then fuel consumption rate increase about 2%.And oil consumption rate not only influences engine performance, also influences its life cycle cost simultaneously.With the Aviation Fuel calculation of price of calendar year 2001, only 1%SFC just can save 1.6 hundred million dollars in 2003 for the U.S..
The stability of tip clearance during to engine operation also has certain influence, as PW4000 engine surge problem.In recent years, surge worldwide takes place in PW4000 motor repeatedly, and these surges mostly occur and taking off and ramp-up period, particularly reaches after the takeoff thrust in 40 ~ 60 seconds.On August 7 calendar year 2001, one 767 domestic aircraft causes engine stalling in takeoff phase because of separate unit PW4000 motor generation surge, and aircraft makes a return voyage.From 1992 so far, 209 high thrust surges worldwide take place in this Engine Series altogether.According to the data that Hewlett-Packard provides, from 1992 so far, 11 on-mechanical reason surges takeoff phase take place in China altogether, concentrate on the B747 and two kinds of types of MD11 that uses the PW4000 motor.Here said surge all is meant the 3rd class surge, and is irrelevant with mechanical deterioration, control imbalance, and relevant with what tip clearance behind the high-pressure compressor.
From above-mentioned introduction as can be seen the research contents of tip clearance many, involve a wide range of knowledge.The active control technology of tip clearance is huge to the reliability and the Economy meaning that improve aeroengine.The pneumatic design of modern aeroengine and test method can make the gas compressor of motor and turbine efficiency reach more than 90%, want that to improve engine efficiency be very difficult by improving pneumatic design again.Therefore, in order to improve the performance of motor, the tip clearance of further studying motor is very necessary.
2.2 domestic and international research progress
Since nineteen fifties, domestic and international many scholars have carried out the research work of tip clearance in succession.Great majority research all is at the test of aspects such as casing processing, blade profile optimization and numerical value research.At present, the controlling method of tip clearance can be divided in the world: active gap control and passive gap control.
One class is the active gap control, and it can be divided into two kinds again: a kind of is the enclosed gap control, and it is to utilize advanced motor tip clearance measurement means, measures the gap width of certain operating mode, with the optimum value of feedback control circuit control gap; Another kind is an open type gap ACTIVE CONTROL, by finding out the accurate rule that tip clearance changes, when engine operating condition changes, calculates gap length this moment with airborne computer, in time adjusts outside required air quantity, carries out the control of best clearance.Two kinds initiatively clearance control method all be working state according to motor, the swell increment of controller lock or rotor artificially, make the thermal response of rotor and stator reach coupling preferably, as far as possible little in high cruise state gap, and disturb friction in the unlikely generation of other state.The control of Britain CFM56-3 engine high pressure turbine clearance utilizes this method to realize.
And another kind of be passive gap control, i.e. the gap control technology of not regulating with engine working conditions.It is main that force-bearing situation under the different operating state carries out serious analysis to rotor and stator, especially the thermal change of machine lock under various operating modes carried out well-designed, in the hope of change, heat between the stator cooperates appropriately, and the gap is kept in allowed limits.The past motor of development all adopts this method.It mainly is the radial clearance when reducing engine operation by the approach such as alloy machine lock that reduce fit up gap, the double-deck machine lock of employing or low linear expansion coefficient.For example, the CF6 of U.S. GE company increases a tangential connecting rod at preceding installation joint place, makes the maximum local deformation of gas compressor machine lock be reduced to 1mm by 1.8mm, thereby reduces the gas compressor gap.The JT9D of U.S. Pu Hui company sprays ceramic coating on the covering compression ring, applies with coat of silicon carbide on the blade tip again, but to improve the running-in ability between ring and the blade.
2.3 the challenge that faces
In the ACTIVE CONTROL field of tip clearance, especially the development of enclosed gap control is faced with the limitation of tip clearance sensor.In recent years for measuring and control the tip clearance of aero-turbine, external aeronautical research mechanism has developed multiple clearance measuring method, now commonly used have the electrical resistivity survey skill of handling needles, capacitance method, electric vortex method, laser probe method or the like, and these methods all have its different characteristics.
What the electrical resistivity survey skill of handling needles adopted is the blade tip discharge mode, promptly relies on motor that the probe of impressed DC voltage is radially moved, and when probe and blade tip generation electric discharge phenomena, probe is to the difference tip clearance of the distance of casing internal surface when stroke that probe moves and static state.It only is applicable to temperature below 600 ℃, rotating speed more than 6000r/min, and the pollution that probe is subjected to foreign matter and oil easily causes obstruction.Because it is a contact type measurement, in case motor stops in emergency, probe is withdrawn less than home, just breaks down easily.
Capacitance method is to measure by the electric capacity that forms between the casing of insulated motor and rotator tip, the electric capacity that records be electrode geometry, two die openings from and the function of two interpolar media.The main feature of capacitance method: highly sensitive, the natural frequency height, Bandwidth, dynamic response performance is good, can the number megahertzes frequency modulation under proper functioning; Power is little, and impedance is high.But its precision is subjected to the influence of factor in many ways, variation, environmental disturbances (magnetic field, electrical spark), probe and the casing temperature distortion of the permittivity of medium, calibration error etc. during as measurement.Insulation is the specific question of capacitance method, because the internal resistance of electric capacity itself is very high, thereby insulation is had higher requirement.In addition, when material property is bad, its insulation resistance will change with temperature and humidity, thereby cause that sensor output produces zero drift slowly.
Electric vortex method is to adopt the Metal Cutting magnetic line of force to produce the method for changes of magnetic field, and electric convolution is surveyed this covering device of spacing and mainly is made of probe and testing circuit two-part.The method is subjected to the influence of blade material bigger, and leaf apex end surface also needs certain thickness.Because sensor output is along with variations such as blade tip shape, installment state and ambient temperatures, therefore, need calibration in advance, make its suitable Environmental Conditions.In addition, the resistance to heat of sensor relatively poor (about 400 ℃).Being used for the turbine high-temperature component at present still has because of difficulty.And probe diameter is greater than 25mm, and the casing bore size is excessive, and inconvenience is installed.
The laser probe method is one laser beam to be projected on the blade tip of rotor blade by optical fiber, when tip clearance changes, because the light return path difference of reflection, the light spot position on the luminous point receiver changes, the gap that its variable quantity promptly draws rotator tip through computing.Because operating sensor under the situation of High Temperature High Pressure and big vibration, therefore needs optical system is protected, and prevents to pollute and instrument damage.
More than several method of measurement represented the state-of-the-art technology of domestic and international clearance measurement basically.Yet the shortcoming of these methods is as follows:
1. vibrating under the environment big, that temperature is high, pressure is big the poor reliability of mechanical transmission.
2. complexity, weight are big and involve great expense as a result for measuring probe.
3. under casing/probe vibrational state or under rotor rotation/eccentric state,, probe and blade tip make probe be easy to damage owing to intermittently contacting.
4. the tip clearance of linear leaf be can only measure, single tip clearance or average tip clearance value can not surveyed.
And when adopting open type gap ACTIVE CONTROL system, the wearing and tearing in the motor using process and the sudden change of state all can cause the decrease in efficiency of tip clearance control, if even when too small (negative value) of gap control,, will cause fatal crass's major accident because of blade scraping casing inwall fractures.
This patent has proposed a kind of turbine vane tip interval ACTIVE CONTROL system, and this system combines the characteristics of enclosed gap control and open type clearance control system.This patent improves and has developed aero-turbine blade tip fast active control system on existing achievement in research basis, combines with quick, stable actuator and can improve the Economy of motor significantly.
Three, summary of the invention
This patent has proposed a kind of novel type aeroengine turbine blade tip gap active control system.This system combines the characteristics of enclosed gap control and open type clearance control system.Because the tip clearance sensor under the prior art condition can't satisfy the needs of engineering practical application, existing sensors (sensors such as rotating speed, temperature, pressure) combines with airborne computer on this system's employing motor, and computational analysis goes out the tip clearance value of turbine.This part has the characteristics of open type clearance control system; When the tip clearance control unit was controlled according to the tip clearance value that calculates, displacement transducer fed back to control unit with the gap control amount of actuator, and this part has the characteristics of enclosed clearance control system.
Type aeroengine turbine blade tip gap active control system (as shown in Figure 1) comprising: airborne computer, tip clearance control unit, actuator, displacement transducer, fly to control sensors such as sensor and rotating speed, temperature, pressure.Wherein, flying to control sensor comprises: the pilot controls Thrust Level Angel sensor, the control stick angle transducer of aircraft.The sensor of motor comprises: speed probe, temperature transducer, pressure transducer.Highly, velocity transducer also is that airborne computer carries out motor and aircraft state is controlled requisite sensor.And the displacement transducer of actuator can come development and Design according to the displacement transducer in the engine tail nozzle area control system.Therefore, the sensor that is comprised in the control system has all obtained the checking of practical application, characteristics such as the maturation that possesses skills, stable height.
The working principle of the turbine blade-tip gap ACTIVE CONTROL system that this patent proposes is: airborne computer according to the data in real time of various sensors calculate the tip clearance value of turbine.The tip clearance control unit is according to the displacement amount of the tip clearance value control executing mechanism that calculates, and then realized the ACTIVE CONTROL of tip clearance.In order to improve the control accuracy of tip clearance, this system utilizes the feedback of displacement transducer that actuator is carried out closed loop control.The radial displacement of the actuator that the displacement sensor temperature of actuator is lower, it and airborne computer combine, and then draw the turbine blade-tip gap value indirectly, so just solved the limitation that tip clearance sensor that the enclosed gap control faces can't directly be measured the tip clearance value effectively.When aircraft carried out maneuvering flight, the engine rotor of high speed rotating certainly will cause the non-uniform change of tip clearance under the influence of gyroscopic effect.In this case, airborne computer can utilize the calculated signals of control stick angle transducer to analyze the non-uniform change amount of tip clearance, and the tip clearance control unit carries out the non-homogeneous control of tip clearance again.Prerequisite is that actuator has the ability that the non-homogeneous tip clearance of control changes.
The type aeroengine turbine blade tip gap active control system that this patent proposes combines the characteristics of enclosed gap control and open type clearance control system.Can't reach under the situation of engineering practical application at existing tip clearance sensor, native system utilizes the sensor on motor and the aircraft to realize the ACTIVE CONTROL of tip clearance in conjunction with airborne computer.Therefore, novel type aeroengine turbine blade tip gap active control system has advantages such as precision is good, feasibility is high, structural modification is little, technical risk is little.
Four, description of drawings
As Fig. 1 is the schematic representation of turbine blade-tip gap ACTIVE CONTROL system.
Five, embodiment
The realization of the turbine blade-tip gap ACTIVE CONTROL system that this patent proposes is relatively easy.Included sensor all is to install on aircraft and the motor in the system, and after actuator's Installation and Debugging, important process is exactly the algorithm and the system combination of computer.Airborne computer must promptly be handled the signal of various sensors, and utilizes advanced turbine blade-tip gap routine analyzer to calculate real-time tip clearance value.At present, the routine analyzer of turbine blade-tip gap has been developed one dimension, two dimension even three-dimensional routine analyzer.Though but wherein the two and three dimensions computer program has advantage of high precision, it is to the performance requirement height of computer, and real-time is also bad.Therefore the turbine blade-tip gap routine analyzer of airborne computer employing should be selected the one dimension program.Next, also need airborne calculating, tip clearance control unit and execution architecture to be integrated into a complete turbine blade-tip gap ACTIVE CONTROL system by great deal of experimental.Be necessary the feasibility of checking this programme on the turbine blade-tip ACTIVE CONTROL of steam turbine earlier.Carry out the experimental study of ground gas turbine and marine gas turbine after the improvement again.Reached after the requirement of aeroengine to aspects such as precision, real-time, reliabilities, be applied to the quick tip clearance ACTIVE CONTROL of aero-turbine again.
Claims (3)
1, a kind of new-type aeroengine turbine blade tip gap active control system.It is characterized in that this system combines the characteristics of enclosed gap control and open type clearance control system.
2, type aeroengine turbine blade tip gap active control according to claim 1 system, it is characterized in that airborne computer according to existing sensors on the motor (sensors such as rotating speed, temperature, pressure) signal, and utilize advanced turbine blade-tip gap routine analyzer to calculate the tip clearance value in real time.
3, type aeroengine turbine blade tip gap active control according to claim 1 system, when it is characterized in that the tip clearance control unit carries out the enclosed gap control according to the tip clearance value that calculates, displacement transducer feeds back to control unit with the gap control amount of actuator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710107216 CN101050712A (en) | 2007-05-24 | 2007-05-24 | Positive control for aviation engine turbine blade-tip gap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710107216 CN101050712A (en) | 2007-05-24 | 2007-05-24 | Positive control for aviation engine turbine blade-tip gap |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101050712A true CN101050712A (en) | 2007-10-10 |
Family
ID=38782290
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200710107216 Pending CN101050712A (en) | 2007-05-24 | 2007-05-24 | Positive control for aviation engine turbine blade-tip gap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101050712A (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103133060A (en) * | 2011-11-25 | 2013-06-05 | 中航商用航空发动机有限责任公司 | Method for controlling gap between blade tip of turbine casing and blade tip of turbine rotor blade |
| CN103775139A (en) * | 2012-10-26 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Gap control system and method for turbine engine |
| CN104713731A (en) * | 2015-03-02 | 2015-06-17 | 南京航空航天大学 | Aero-turbine active clearance control cartridge receiver model confirmatory experiment table |
| CN105387823A (en) * | 2015-11-30 | 2016-03-09 | 西北工业大学 | Microwave short-range measurement method based on reflectometer sensor |
| CN105507957A (en) * | 2014-10-10 | 2016-04-20 | 航空技术空间股份有限公司 | Axial turbomachine compressor outer casing with seal |
| CN109406114A (en) * | 2017-05-09 | 2019-03-01 | 中国航空制造技术研究院 | A kind of aeroengine rotor blade working condition checkout gear and detection method |
| CN109558041A (en) * | 2018-09-28 | 2019-04-02 | 天津大学 | Tip clearance signal acquisition, processing and the transmission method accelerated based on GPU |
| CN109556556A (en) * | 2018-12-18 | 2019-04-02 | 中国航发沈阳发动机研究所 | A kind of high-pressure turbine in cold conditions assembling process turns stator tip clearance measurement method |
| CN110006655A (en) * | 2018-01-05 | 2019-07-12 | 中国航发商用航空发动机有限责任公司 | Aeroengine compressor monitoring method and monitoring system |
| CN112302733A (en) * | 2020-11-05 | 2021-02-02 | 南京航空航天大学 | Active control module for enhancing performance of aviation turboprop engine |
| CN112612082A (en) * | 2019-10-04 | 2021-04-06 | 日本麦可罗尼克斯股份有限公司 | Optical probe, optical probe array, inspection system, and inspection method |
| CN112855352A (en) * | 2019-11-28 | 2021-05-28 | 中国航发商用航空发动机有限责任公司 | Calculation method and control method for real-time blade tip clearance of high-pressure turbine |
| CN113446069A (en) * | 2020-03-26 | 2021-09-28 | 中国航发商用航空发动机有限责任公司 | Passive control device for blade tip clearance of aero-engine and aero-engine |
| CN113639625A (en) * | 2021-07-14 | 2021-11-12 | 南京理工大学 | Dynamic testing system for seat ring clearance of large-scale rotating machinery |
| CN115324662A (en) * | 2022-05-30 | 2022-11-11 | 天津大学 | Fault diagnosis method based on blade tip clearance signal rotor dynamic characteristic analysis |
-
2007
- 2007-05-24 CN CN 200710107216 patent/CN101050712A/en active Pending
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103133060A (en) * | 2011-11-25 | 2013-06-05 | 中航商用航空发动机有限责任公司 | Method for controlling gap between blade tip of turbine casing and blade tip of turbine rotor blade |
| CN103133060B (en) * | 2011-11-25 | 2015-10-21 | 中航商用航空发动机有限责任公司 | Gas turbine engine and control the method in gap between turbine casing and rotor blade |
| CN103775139A (en) * | 2012-10-26 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Gap control system and method for turbine engine |
| CN103775139B (en) * | 2012-10-26 | 2015-09-23 | 中航商用航空发动机有限责任公司 | The clearance control system of turbogenerator and the clearance control method of turbogenerator |
| CN105507957A (en) * | 2014-10-10 | 2016-04-20 | 航空技术空间股份有限公司 | Axial turbomachine compressor outer casing with seal |
| CN104713731A (en) * | 2015-03-02 | 2015-06-17 | 南京航空航天大学 | Aero-turbine active clearance control cartridge receiver model confirmatory experiment table |
| CN104713731B (en) * | 2015-03-02 | 2017-06-13 | 南京航空航天大学 | A kind of aero-turbine active clearance controls casing model confirmatory experiment platform |
| CN105387823A (en) * | 2015-11-30 | 2016-03-09 | 西北工业大学 | Microwave short-range measurement method based on reflectometer sensor |
| CN105387823B (en) * | 2015-11-30 | 2018-05-01 | 西北工业大学 | Microwave low coverage measuring method based on reflection flowmeter sensor |
| CN109406114A (en) * | 2017-05-09 | 2019-03-01 | 中国航空制造技术研究院 | A kind of aeroengine rotor blade working condition checkout gear and detection method |
| CN110006655A (en) * | 2018-01-05 | 2019-07-12 | 中国航发商用航空发动机有限责任公司 | Aeroengine compressor monitoring method and monitoring system |
| CN109558041A (en) * | 2018-09-28 | 2019-04-02 | 天津大学 | Tip clearance signal acquisition, processing and the transmission method accelerated based on GPU |
| CN109558041B (en) * | 2018-09-28 | 2021-09-24 | 天津大学 | GPU acceleration-based blade tip clearance signal acquisition, processing and transmission method |
| CN109556556B (en) * | 2018-12-18 | 2022-02-22 | 中国航发沈阳发动机研究所 | Method for measuring blade tip clearance of high-pressure turbine rotor stator in cold-state assembly process |
| CN109556556A (en) * | 2018-12-18 | 2019-04-02 | 中国航发沈阳发动机研究所 | A kind of high-pressure turbine in cold conditions assembling process turns stator tip clearance measurement method |
| CN112612082B (en) * | 2019-10-04 | 2023-08-29 | 日本麦可罗尼克斯股份有限公司 | Optical probe, optical probe array, inspection system, and inspection method |
| CN112612082A (en) * | 2019-10-04 | 2021-04-06 | 日本麦可罗尼克斯股份有限公司 | Optical probe, optical probe array, inspection system, and inspection method |
| CN112855352B (en) * | 2019-11-28 | 2022-03-22 | 中国航发商用航空发动机有限责任公司 | Calculation method and control method for real-time blade tip clearance of high-pressure turbine |
| CN112855352A (en) * | 2019-11-28 | 2021-05-28 | 中国航发商用航空发动机有限责任公司 | Calculation method and control method for real-time blade tip clearance of high-pressure turbine |
| CN113446069A (en) * | 2020-03-26 | 2021-09-28 | 中国航发商用航空发动机有限责任公司 | Passive control device for blade tip clearance of aero-engine and aero-engine |
| CN113446069B (en) * | 2020-03-26 | 2023-06-20 | 中国航发商用航空发动机有限责任公司 | Aeroengine blade tip clearance passive control device and aeroengine |
| CN112302733A (en) * | 2020-11-05 | 2021-02-02 | 南京航空航天大学 | Active control module for enhancing performance of aviation turboprop engine |
| CN113639625A (en) * | 2021-07-14 | 2021-11-12 | 南京理工大学 | Dynamic testing system for seat ring clearance of large-scale rotating machinery |
| CN115324662A (en) * | 2022-05-30 | 2022-11-11 | 天津大学 | Fault diagnosis method based on blade tip clearance signal rotor dynamic characteristic analysis |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101050712A (en) | Positive control for aviation engine turbine blade-tip gap | |
| US7824147B2 (en) | Airfoil prognosis for turbine engines | |
| CA2915367A1 (en) | Torque sensor monitoring for gas turbine engine | |
| CN110319922B (en) | Blade torsional vibration displacement measurement method based on blade tip timing principle | |
| JP2011508158A (en) | Compressor and gas turbine engine with plasma actuator | |
| CN110566289B (en) | Method of operating a turbomachine | |
| Johnston et al. | Unsteady wing surface pressures in the wake of a propeller | |
| Woike et al. | Testing of a microwave blade tip clearance sensor at the NASA Glenn Research Center | |
| Brandstetter et al. | UHBR open-test-case fan ECL5/CATANA part 1: geometry and aerodynamic performance | |
| Walker et al. | Periodic transition on an axial compressor stator: Incidence and clocking effects: Part I—Experimental data | |
| Binghui et al. | An optical fiber blade tip clearance sensor for active clearance control applications | |
| Kulkarni et al. | Vibratory response characterization of a radial turbine wheel for automotive turbocharger application | |
| Carta et al. | Experimentally determined stability parameters of a subsonic cascade oscillating near stall | |
| Yan et al. | Real-time detection of damage evolution and failure of EB-PVD thermal barrier coatings using an environmental simulator with high-temperature and high-speed rotation | |
| CN111288884A (en) | Device and method for measuring blade tip clearance based on closed environment | |
| Capece et al. | Unsteady aerodynamic interactions in a multistage compressor | |
| Geisheimer et al. | A microwave blade tip clearance sensor for active clearance control applications | |
| Sanders et al. | Multi-Blade Row Interactions in a Transonic Axial Compressor: Part II—Rotor Wake Forcing Function and Stator Unsteady Aerodynamic Response | |
| Ott et al. | Experimental and numerical study of the time-dependent pressure response of a shock wave oscillating in a nozzle | |
| Solomon | Effects of turbulence and solidity on the boundary layer development in a low pressure turbine | |
| Chana et al. | The development of a hot section eddy current sensor for turbine tip clearance measurement | |
| Cardinale et al. | Experimental verification of turboblading aeromechanics | |
| CN211626374U (en) | Blade tip clearance measuring device based on closed environment | |
| CN114719809A (en) | Method and apparatus for real-time clearance assessment using pressure measurements | |
| Cherrett et al. | Unsteady three-dimensional flow in a single-stage transonic fan: Part I—Unsteady rotor exit flow field |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |