CN103852445A - Design method of optical probe for measuring laser absorption spectrum - Google Patents
Design method of optical probe for measuring laser absorption spectrum Download PDFInfo
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- CN103852445A CN103852445A CN201410101742.3A CN201410101742A CN103852445A CN 103852445 A CN103852445 A CN 103852445A CN 201410101742 A CN201410101742 A CN 201410101742A CN 103852445 A CN103852445 A CN 103852445A
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Abstract
本发明提供了一种用于激光吸收光谱测量的嵌入式光学探头，包括发射探头和接收探头。发射探头包含第一壁面嵌入部件、第一过渡部件、波纹管结构和第一准直器；接收探头包含第二壁面嵌入部件、第二过渡部件和第二准直器。通过对探头内腔充入干燥氮气，可方便实现对窗口的保护气膜并对流场外的自由光路进行净化。本发明的光学探头具有结构紧凑、抗诱导振动、通用性强以及净化和气膜冷却实现方便等优点。
The invention provides an embedded optical probe for laser absorption spectrum measurement, which includes a transmitting probe and a receiving probe. The transmitting probe includes a first wall embedded part, a first transition part, a bellows structure and a first collimator; the receiving probe includes a second wall embedded part, a second transition part and a second collimator. By filling the inner cavity of the probe with dry nitrogen, it is convenient to realize the protective gas film on the window and to purify the free optical path outside the flow field. The optical probe of the invention has the advantages of compact structure, anti-induced vibration, strong versatility, convenient realization of purification and air film cooling, and the like.
Description
Technical field
The invention belongs to flow field field of optical measuring technologies, relate to tunable diode laser absorption spectroscopy technology, particularly a kind of built-in optical probe technologies of measuring for laser absorption spectrum.
Background technology
Due to the alternative of noncontact characteristic and monitoring composition, laser measuring technique has become burning and has advanced the important development direction of flow field diagnostic techniques.Wherein tunable diode laser absorption spectroscopy (tunable diode laser absorption spectroscopy TDLAS) technical development is relatively ripe, the crucial flow field parameter such as temperature that can measurement gas, concentration of component, speed, mass rate.Measuring system based on TDLAS has that time response is fast, data analysis is simple, signal intensity is high, light beam can be carried out by optical fiber the significant advantages such as long-distance transmissions, relative low price.
Since the nineties in last century, all actively develop the research of TDLAS application taking Stanford university, NASA, Physical Sciences company, USAF etc. as numerous R&D institutions, government, enterprise and the department of the military of representative, successively carried out successful engineering application in flow fields such as shock tube, aeromotor, scramjet engine, pulse-knocking engine, steam turbine, internal combustion engine, industrial combustion furnaces.Since entering the new century, TDLAS technology causes the extensive concern of scientific research institutions of China and industrial enterprise, develop comparatively rapid, the applied research that has started at present to relate to burning and advanced flow field, accumulated certain technical foundation and engineering application experience, but Research Ability and level still there is larger gap.
Optic probe is one of Primary Component of TDLAS engineering application, and its function is by laser beam datum transmitting, enters tested flow field, and the light beam through flow field is caught, and comprises transmitting probe and receiving transducer.In Actual combustion flow fields such as engines, be faced with all serious harsh conditions such as limited of the rugged surroundings such as vibratory impulse, pneumatic refraction, High Temperature High Pressure and installing space and optics entrance, optic probe will play vital effect to obtaining of measuring-signal, directly determine the success or failure of measuring.
Following document has been directly involved in the design of optic probe.
1, Physical Sciences company is under the subsidy of USAF, in the temperature in the supersonic combustion wind-tunnel application TDLAS sensor measurement flow field in Wright-Patterson air base, speed and water vapor concentration (Upschulte B L, Miller M F, Allen M G, et al..Continuous water vapor mass flux and temperature measurements in a model Scramjet combustor using a diode laser sensor[R] .Reno:37th AIAA Aerospace Sciences Meeting & Exhibit.AIAA99-0518.).Installation of sensors, in the firing chamber of wind-tunnel, has the hole of 4 2.54cm in combustion chamber wall surface, for optical window is installed, for protection optical window avoids high temperature loss, have independent air hole on the side of window mounting hole, forms air film at window front end.Probe is arranged on wall outside independent with window.Transmitting probe comprises collimating apparatus and bracing frame, and bracing frame does not have the regulatory function of emission angle, and light beam is first received by detector with concave mirror focus after reaching receiving transducer again.
2, cooperate with Pratt & Whitney aircraft company of the U.S. in the Hanson laboratory of Stanford university, on PW6000 commercial aviation engine, apply MAF (the Lyle K H of TDLAS sensor measurement air intake duct, Jeffries J B and Hanson R K.Diode laser sensor for air mass flux based on oxygen absorption2:non-uniform flow modeling and aero-engine tests[J] .AIAA Journal, 2007,45.).The external bellmouth in upstream of engine inlets and " jockey pulley ", for setting pressure and temperature probe.TDLAS installation of sensors is at bellmouth, there is no special optical channel but used pressure probe mounting hole optical window is installed on bellmouth.Probe is arranged on wall outside independent with window, and transmitting collimating apparatus is arranged on business multiaxis adjustment rack, can carry out the two-dimensional adjustment of emission angle, and receiving transducer comprises focusing surface mirror and detector, for catching light beam.
3, the Hanson laboratory of Stanford university is under the subsidy of NASA, on the direct-connected ultra-combustion ramjet testing table at Langley center, apply mass rate (the Chang L S of TDLAS sensor measurement distance piece air-flow, Jeffries J B and Hanson R K.Mass flux sensing via tunable diode laser absorption of water vapor[C] .Orlando:49th AIAA Aerospace Science Meeting Including the New Horizons Forum and Aerospace Exposition, AIAA2011-1093.).The design of the optic probe in the document and document 2 are similar.
The optic probe of document 1 is except emission angle is unadjustable, and its design is similar with document 2 and document 3.In general, the design in document exists following not enough:
1) probe is arranged on wall outside, separate with optical window, causes overall dimensions larger, and this is at practical flow fields such as engines, because the restriction in space often brings the difficulty of installation.Because flow field external circuits is long and sealing difficulty, be not easy to it to purify in addition.
2) probe size and quality are large and be arranged on wall outside, and in the time of engine operation, induced vibration is comparatively serious, has increased the difficulty of beam-capturing.There is fragility in this probe installation form simultaneously.As just occurred occurring because vibration causes the situation that business adjustment rack coupling bolt comes off in the experiment of document 2.
3) receiving transducer adopts focusing surface mirror to add the mode of detector, although be conducive to strengthen the capture ability of light beam, detector needs strict thermal protection measure, and because light path is turned back, has increased installation difficulty and be also unfavorable for reducing physical dimension.
4) although the mentality of designing of 3 sections of documents is similar, due to only, for specific installation environment, device and structural difference used are larger, and in particular for realizing speed measuring function, probe is axial and wall normal direction is at a certain angle, shortcoming versatility.
Summary of the invention
The object of the invention is to design a kind of built-in optical probe of compact conformation on the basis of foreign design philosophy and use experience, there is higher anti-vibration ability and stronger versatility, the engineering application power that promotes China TDLAS technology, promotes the progress of advanced jet flow field diagnostic techniques.
The invention provides a kind of built-in optical probe of measuring for laser absorption spectrum, comprise transmitting probe and receiving transducer two parts, it is characterized in that:
Transmitting probe comprises the first wall built in items, First Transition parts (5), bellows structure and first collimator, wherein, the first wall built in items comprises cavity (1), optical window (2), jacking block (3), screw nut (4), optical window (2) front end has a conical surface, optical window (2) and the inner conical surface of cavity (1) are held out against by jacking block (3) by screwing nut (4), First Transition parts (5) connect the first wall built in items and bellows structure, erection bolt is through First Transition parts (5) and cavity (1), be connected with wall, First Transition parts have light hole and air hole in (5), the outside valve (6) that connects of air hole, bellows structure comprises derby (7), corrugated tube (8), lower derby (9), adjusting bolt (10) and stage clip (11), upper derby (7) is bolted to First Transition parts (5), the internal thread of lower derby (9) connects first collimator (12), by changing adjusting bolt (10), the decrement of stage clip (11) is adjusted to beam emissions angle,
Receiving transducer comprises the second wall built in items, the second transition member (5) and the second collimating apparatus;
The second wall built in items in receiving transducer has identical structure with the first wall built in items in transmitting probe, can exchange.
Advantage of the present invention is:
1) compact conformation.Owing to having adopted the integrated design of probe and window, significantly reduce the physical dimension of probe.
2) anti-induced vibration.Owing to adopting embedded design, quality and the size of wall outside significantly reduce, and can strengthen the ability of opposing induced vibration.
3) highly versatile.Thermometric and holes probe axially all vertical with wall, and have identical wall interface size, the wall embedded part that transmits and receives probe is interchangeable, has stronger versatility.
4) the cooling realization of purification and air film is convenient, can be realized and being purified and the cooling dual-use function of air film by an inlet channel.
Brief description of the drawings
Fig. 1 is the receiving transducer schematic diagram for thermometric;
Fig. 2 is the transmitting probe schematic diagram for thermometric;
Fig. 3 is the receiving transducer schematic diagram for testing the speed;
Fig. 4 is the transmitting probe schematic diagram for testing the speed;
Fig. 5 is the installation cut-open view of probe at engine wall.
Embodiment
By reference to the accompanying drawings optic probe is described in further detail.Fig. 1-Fig. 4 is respectively for thermometric with for the reception of testing the speed, the schematic diagram of transmitting probe.
Optic probe adopts modular design, realizes as far as possible the interchangeability of assembly.Consider the requirement such as thermal protection and vibration and shock resistant of integrated, the sensor of the adjusting of pneumatic refraction, transmit direction of beam direction and locking, optical window and probe, realize under vibration and high temperature flow field environment and keep reliable optical alignment ability.
In order to reduce thermal protection demand, make structure more compact simultaneously, receiving transducer has been abandoned the structure that focusing surface mirror adds detector, but the light beam through flow field is focused on and enters multimode optical fiber by collimating apparatus, then enters detector by multimode optical fiber long-distance transmissions.This design makes the structure of transmitting probe and receiving transducer similar, is convenient to the versatility of parts.The wall embedded part that transmits and receives probe is identical, has so just realized the interchangeability of wall embedded part.The effect of collimating apparatus is similar, and the Gaussian beam collimation transmitting that transmitting collimating apparatus is sent single-mode fiber enters flow field, receives collimating apparatus collimated light beam is focused on and is coupled into multimode optical fiber.For accurately by beam emissions to the position angle of expectation and keep optical alignment, transmitting probe need to possess adjusting and the locking function of emission angle.The impact bringing for adapting to as far as possible the pneumatic refraction effect of light beam in flow field and mechanical vibration, receiving transducer possesses enough large clear aperature and numerical aperture.
During due to velocity survey, be to produce doppler shift effect, in flow field, laser propagation direction and mobile normal direction have certain angle requirement, therefore must on the runner with certain length, just can complete measurement; Temperature and concentration of component are measured without this particular/special requirement, therefore can complete measurement in arbitrary cross section of runner.For adapting to different measurement demands, probe has two kinds of fundamental types: temperature probe and holes probe.Temperature probe is suitable for not needing the occasion of velocity survey, and holes probe is suitable for only needing velocity survey or speed and other to measure simultaneously-measured occasion.Need for ease of standardization and unified interface, two kinds of probes all adopt the mode that is axially perpendicular to wall to install, and its difference is that the optical window of holes probe has changed the direction of propagation of light beam.
Temperature probe is identical with holes probe structure, and its main difference is that the optical window design of two kinds of probes is different, narrates below as an example of the holes probe (comprising transmitting probe and receiving transducer) of Fig. 3 and Fig. 4 example.
Transmitting probe comprises the first wall built in items, First Transition parts (5), bellows structure and first collimator.The first wall built in items comprises cavity (1), optical window (2), jacking block (3), screws nut (4).Optical window (2) produces the light beam turning angle of expecting, and by flow field and external environment condition isolation.Optical window (2) front end has a conical surface, optical window (2) and the inner conical surface of cavity (1) is held out against by jacking block (3) by screwing nut (4).First Transition parts (5) connect the first wall built in items and bellows structure, and erection bolt, through First Transition parts (5) and cavity (1), is connected with wall.First Transition parts have light hole and air hole in (5), the outside valve (6) that connects of air hole.Bellows structure comprises derby (7), corrugated tube (8), lower derby (9), adjusting bolt (10) and spring (11).Corrugated tube (8) and upper derby (7), lower derby (9) are welded together, upper derby (7) is bolted to First Transition parts (5), and the internal thread of lower derby (9) connects first collimator (12).By changing adjusting bolt (10), the decrement of spring (11) is adjusted to beam emissions angle.
Fig. 5 has provided the installation cut-open view of probe at engine wall.Transmitting probe is in the time of work, drying nitrogen is by valve (6), be filled with the space between first collimator (12) and optical window (2), free space light path outside stream field purifies, nitrogen stream passes through the micropore of cavity (1) sidewall along the minim gap flow direction probe front end between cavity (1) and probe mounting hole, form air film at probe front end, window is carried out to thermal protection (seeing local amplifier section).
Receiving transducer comprises the second wall built in items, the second transition member (5) and the second collimating apparatus;
The second wall built in items in receiving transducer has identical structure with the first wall built in items in transmitting probe, can exchange.
The design procedure of a kind of built-in optical probe of measuring for laser absorption spectrum of the present invention is:
The design of step 1, the first/the second wall built in items
Cavity is selected high-quality stainless steel material, and chamber wall external diameter 15mm is being reduced to 14.8mm apart from the external diameter of front end face 15mm part, internal diameter 12mm, and long 25mm, there is the chamfering of 45 ° front end and optical window cooperation place.At the aperture of uniform 4 the 1mm diameters of chamber wall apart from front end face 14mm.Installed surface is rectangle, length 52mm, width 40mm, thickness 8mm.The threaded hole of diameter 24mm is opened at installed surface center, and degree of depth 4mm and screws nut and coordinates; 4 jiaos have the through hole of diameter 6.2mm, for being connected with wall.For making laser beam that collimating apparatus is sent can enter the center on optical window inclined-plane, chamber wall axis departs from the symcenter 3.3mm of installed surface along the length direction of rectangle.
Optical window is selected ultraviolet level fused silica material, diameter 12mm, height 12.7mm, the inclined-plane that there is 54.5 °, an inclination angle one end (now, for the near infrared light beam of wavelength 1360nm by inclined-plane incident after, exit direction and the method for section are to 30 ° of deviations), bevel altitude 7.7mm, the window other end has the chamfering of 45 °.
Jacking block material is duralumin, and cross section is semicircle, radius 6mm.Screw nut diameter 24mm, thickness 3mm, there is the fine thread of tooth apart from 0.5mm in outside.
The design of step 2, bellows structure
Outside diameter of bel 24mm, state of nature length 16mm, upper and lower derby diameter is selected stainless steel material, diameter 40mm, thickness 8mm.Uniform 3 adjusting bolts and high rigidity stage clip outside corrugated tube.The upper surface of upper derby has external diameter 16mm, and the locating ring of high 2mm, for the location that is connected with transition member.
The type selecting of step 3, collimating apparatus
The first and second collimator function are similar, but require different.The Gaussian beam collimation transmitting that first collimator sends single-mode fiber enters flow field, and the second collimating apparatus focuses on collimated light beam to be coupled into multimode optical fiber.Therefore first collimator mainly considers it is that diameter and the angle of divergence of light beam is little, and in order more effectively to collect light beam, and the second collimating apparatus needs larger clear aperature and numerical aperture.First collimator is selected the F240APC-C of Thorlabs company, external diameter 12mm, FC/APC connector, beam diameter 1.5mm, 0.065 ° of the angle of divergence.The second collimating apparatus is selected the HPUCO-25-1300-M of OZ Optics company, attachment face diameter 33mm, lens diameter 10mm, numerical aperture 0.5.
The design of step 4, transition member
The end face of the first/the second transition member is rectangle, length 52mm, and width 40mm, thickness 12mm, center all has the light hole of diameter 11mm, and a side all has the air hole of diameter 4mm, and valve is installed in air hole outside.4 jiaos of rectangle end face have counterbore, for the bolt through M6, above-mentioned transition member and corresponding wall built in items are bolted to engine wall.The difference of the first excessive parts and the second transition member is: in transmitting probe, the end face being connected with corrugated tube of First Transition parts has diameter 16mm, the mounting hole of degree of depth 2.5mm; And in receiving transducer, the second transition member with second
The end face that collimating apparatus connects has diameter 33mm, the mounting hole of dark 4mm.
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Cited By (6)
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| CN105445223A (en) * | 2015-11-09 | 2016-03-30 | 北京航天易联科技发展有限公司 | Humidity detection device for measuring high-temperature flue gas |
| CN109632664A (en) * | 2018-12-14 | 2019-04-16 | 中国航空工业集团公司北京长城航空测控技术研究所 | It is a kind of for installing the device of optic probe under high temperature and vibration condition |
| CN110954501A (en) * | 2019-12-13 | 2020-04-03 | 中国航空工业集团公司北京长城航空测控技术研究所 | High-temperature-resistant tunable laser absorption spectrum probe structure |
| CN112113660A (en) * | 2020-09-17 | 2020-12-22 | 中国兵器装备集团上海电控研究所 | Calibration and acceptance tool and calibration and acceptance method for optical flame detector |
| CN114002153A (en) * | 2021-11-12 | 2022-02-01 | 西安热工研究院有限公司 | Optical probe fixing device suitable for combustion monitoring of gas turbine |
| CN114608793A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Static pressure measuring device for wind tunnel and static pressure measuring method thereof |
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Cited By (7)
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| CN105445223A (en) * | 2015-11-09 | 2016-03-30 | 北京航天易联科技发展有限公司 | Humidity detection device for measuring high-temperature flue gas |
| CN105445223B (en) * | 2015-11-09 | 2019-07-05 | 北京航天易联科技发展有限公司 | Humidity detector for high-temperature flue gas measurement |
| CN109632664A (en) * | 2018-12-14 | 2019-04-16 | 中国航空工业集团公司北京长城航空测控技术研究所 | It is a kind of for installing the device of optic probe under high temperature and vibration condition |
| CN110954501A (en) * | 2019-12-13 | 2020-04-03 | 中国航空工业集团公司北京长城航空测控技术研究所 | High-temperature-resistant tunable laser absorption spectrum probe structure |
| CN112113660A (en) * | 2020-09-17 | 2020-12-22 | 中国兵器装备集团上海电控研究所 | Calibration and acceptance tool and calibration and acceptance method for optical flame detector |
| CN114002153A (en) * | 2021-11-12 | 2022-02-01 | 西安热工研究院有限公司 | Optical probe fixing device suitable for combustion monitoring of gas turbine |
| CN114608793A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Static pressure measuring device for wind tunnel and static pressure measuring method thereof |
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