CN102756809B - Opened type airplane hot-gas anti-icing test device - Google Patents
Opened type airplane hot-gas anti-icing test device Download PDFInfo
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- CN102756809B CN102756809B CN201210236602.8A CN201210236602A CN102756809B CN 102756809 B CN102756809 B CN 102756809B CN 201210236602 A CN201210236602 A CN 201210236602A CN 102756809 B CN102756809 B CN 102756809B
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Abstract
The invention discloses an opened type airplane hot-gas anti-icing test device. A positioning end of a gas supply flute-shaped pipe is mounted in a counter positioning hole of a second de-icing cavity board; a second gasket is arranged in a second wing-shaped groove; a first gasket is arranged in a first wing-shaped groove; a conformal end cover assembly is mounted on the first de-icing cavity board; the both ends of a wing-shaped hot-gas anti-icing cavity are respectively mounted between a first de-icing cavity board and the second de-icing cavity board; four fastening and positioning rods pass through corresponding mounting holes of the first de-icing cavity board and the second de-icing cavity board, and are fastened at the both ends of the positioning rod through nuts, so that the wing-shaped hot-gas anti-icing cavity is mounted by clamping the first de-icing cavity board and the second de-icing cavity board clamp. A test device provided by the invention can be used for intensive study on the property that the complex structure of the wing-shaped hot-gas anti-icing cavity influences internal flow heat transmission, so that the influence factors of the heat property of the de-icing cavity can be comprehensively revealed. Therefore, the pre-design of the complex structure of the de-icing cavity and gas supply parameters can be carried out under the condition that the de-icing heat load distribution is known. Furthermore, whether the given de-icing cavity can meet de-icing requirements or not can be subjected to scientific and rapid general performance evaluation.
Description
Technical field
The present invention relates to a kind of experimental set-up that is applicable to the hot air anti-icing chamber internal flow heat transfer characteristic parameter study in aircraft field, more particularly, refer to a kind of open aircraft hot air anti-icing chamber experimental set-up.
Background technology
While flying under aircraft is freezing meteorological conditions, the super-cooling waterdrop of suspension can occur freezing at wing, screw propeller, engine inlets, Windshield and sensor parts surface.Ice formation issues will have a strong impact on the safety of aircraft flight.
Hot air anti-icing system, by from starting power traction high-temperature gas, heats anti-icing surface, is current the most frequently used a kind of anti icing system.Because the energy of hot air anti-icing system is from driving engine, the efficiency that improves hot air anti-icing system for reducing the compensatory loss of energy, to improve engine thrust significant.The raising of hot air anti-icing system effectiveness depends on the in-depth study to mobile in hot air anti-icing chamber and diabatic process.
Aircraft hot air anti-icing chamber is by from starting power traction high-temperature gas, via air feed bourdon's tube, deliver to and in chamber, heat anti-icing surface, be the most frequently used a kind of basic structure of current commercial aircraft anti icing system, comprise that feeder liner ARJ21 and airliner C919 that China is developing adopt this version.But, the various arrangement of bourdon's tube hot gas jet orifice, the diameter of jet orifice and the relative position of spacing, jet orifice and cavity, the relative position of bourdon's tube in chamber etc. of comprising of aircraft hot air anti-icing chamber inner structure factor, internal heat air-flow moves and presents serious three-dimensional character, the heat exchange causing is very complicated, mucosal structure is larger on the heat exchange impact between hot gas and cavity wall face, thereby affects anti-icing chamber heat efficiency.At present for hot air anti-icing mucosal structure, affect the mechanism research of flowing heat transfer also not comprehensive, especially lack experimental study work, make domestic the design of this structure and development to be had to rely on international vendor.In order to break away from as early as possible the dependence to foreign technology, make the independent development hot air anti-icing cavity configuration of China's energy, carrying out of related experiment work is just extremely important, traditional hot air anti-icing chamber experimental installation bears internal pressure in order to guarantee cavity, all make the pattern of tube chamber one and pass through welding fabrication, but the leading edge surface of considering hot air anti-icing chamber is the airfoil structure of continuous variable curvature, tooling cost is very high, and the various structure of paying close attention to mainly concentrates in the transposing of inner bourdon's tube, the present invention discloses a kind of open aircraft hot air anti-icing chamber experimental installation, guaranteeing under the prerequisite of the withstand voltage feature invariant of cavity, realize cavity and different structure, the flexible assembling of caliber bourdon's tube, solve costly experimental set-up Cost Problems.
Summary of the invention
The object of this invention is to provide a kind of open aircraft hot air anti-icing chamber experimental set-up, this experimental set-up can affect internal flow biography thermal property to hot air anti-icing chamber labyrinth and carry out in-depth study, thereby disclose the influence factor of anti-icing chamber thermal behavior comprehensively, realization distributes known in the situation that at Anti-icing Heat Loads, can carry out the pre-designed of anti-icing chamber labyrinth and air feed parameter, and to known anti-icing chamber, can meet anti-icing demand and carry out science Evaluation on Total Performance efficiently.
A kind of open aircraft hot air anti-icing of the present invention chamber experimental set-up, it includes air feed bourdon's tube (2), the first anti-icing chamber plate (3), the second anti-icing chamber plate (4), the first packing ring (6), the second packing ring (7), conformal end-cap assembly (8) and fastening radius stay; Fastening radius stay is arranged between the first anti-icing chamber plate (3) and the second anti-icing chamber plate (4);
The first anti-icing chamber plate (3) is provided with the first through hole (33) and fourth hole (34); In described the first through hole (33), be placed with the end cap seat (81) of conformal end-cap assembly (8); Described fourth hole (34) passes for one end of fastening radius stay;
The positive plate face (31) of the first anti-icing chamber plate (3) is provided with and wing the first identical wing groove (311) of aerofoil profile hot air anti-icing chamber cavity (1); Described the first wing groove (311) is for placing one end of aerofoil profile hot air anti-icing chamber cavity (1);
The second anti-icing chamber plate (4) is provided with fifth hole (46); Described fifth hole (46) passes for the other end of fastening radius stay;
The second anti-icing chamber plate (4) positive plate face (41) be provided with and wing the second identical wing groove (411) of aerofoil profile hot air anti-icing chamber cavity (1); Described the second wing groove (411) is for placing the other end of aerofoil profile hot air anti-icing chamber cavity (1); In described the second wing groove (411), be provided with countersunk head knock hole, described countersunk head knock hole is used for placing the positioning end (21) of air feed bourdon's tube (2);
Air feed bourdon's tube (2) is hollow structure, and middle part is provided with blind hole (25); One end of air feed bourdon's tube (2) is positioning end (21), and the other end of air feed bourdon's tube (2) is inlet end (22); The body (23) of air feed bourdon's tube (2) is provided with a plurality of jet orifices (24);
Conformal end-cap assembly (8) includes end cap seat (81), large sealing packing ring (82), small sealing ring (83), nut (84) and packing ring (85); The center of described end cap seat (81) offers third through-hole (812), and the outside of described end cap seat (81) is provided with dish edge (814); Dish edge (814) is provided with groove (815) and tapped bore (816) is installed, and described groove (815) is for placing large sealing packing ring (82); One end of described end cap seat (81) is external thread section (811), and the other end of described end cap seat (81) is smooth section (813); Nut (84) has been threaded on the external thread section (811) of described end cap seat (81), when nut (84) is installed with end cap seat (81), first in nut (84), put into after packing ring (85), small sealing ring (83), nut (84) is enclosed within on the external thread section (811) of end cap seat (81);
Described nut (84) center is the second through hole (843), is provided with negative thread (841) and Internal baffle (842) in described the second through hole (843), and described Internal baffle (842) is for placing packing ring (85).
The open aircraft hot air anti-icing chamber experimental set-up of the present invention's design, by changing the first anti-icing chamber plate (3), realize the air feed bourdon's tube (2) of different structure and change, guarantee that air feed bourdon's tube (2) is forever perpendicular to the first anti-icing chamber plate (3) and the second anti-icing chamber plate (4) simultaneously.
The open aircraft hot air anti-icing chamber experimental set-up of the present invention's design, the positioning end of air feed bourdon's tube (2) coordinates with a plurality of countersunk head knock holees on the second anti-icing chamber plate (4), has realized the change in location of air feed bourdon's tube (2) in aerofoil profile hot air anti-icing chamber cavity (1).
The advantage of the open aircraft hot air anti-icing of the present invention chamber experimental set-up is:
1. the bourdon's tube 2 of different structure can being connected by conformal end-cap assembly 8 and the first anti-icing chamber plate 3, can realize a plurality of bourdon's tubes 2 and carry out the test of aircraft hot air anti-icing chamber internal flow heat transfer characteristic at aluminum aerofoil profile hot air anti-icing chamber cavity 1, thereby significantly reduce testing cost.
2. conformal end-cap assembly 8, by being sealed and matched of big or small sealing member, packing ring and thread connecting mode, makes the convenient disassembly of conformal end-cap assembly 8 and the first anti-icing chamber plate 3.
3. the knock hole on the bourdon's tube 2 of different structure and the second anti-icing chamber plate 4 is installed, can change the position of bourdon's tube 2 in aluminum aerofoil profile hot air anti-icing chamber cavity 1, realize bourdon's tube 2 with respect to the test of a plurality of distances of aluminum aerofoil profile hot air anti-icing chamber cavity 1 leading edge.
4. utilize two anti-icing chamber plate holders to hold coordinating of aluminum aerofoil profile hot air anti-icing chamber cavity 1 and conformal end-cap assembly 8 and the first anti-icing chamber plate 3, guaranteed the test position of aluminum aerofoil profile hot air anti-icing chamber cavity 1 in experimental set-up of the present invention and the air-tightness of aluminum aerofoil profile hot air anti-icing chamber cavity 1.
5. the installation of the air feed bourdon's tube 2 that the first anti-icing chamber plate 3 of changing the first through hole 33 of diverse location can be realized different structure on the second anti-icing chamber plate 4 different knock holees.
Accompanying drawing explanation
Fig. 1 is the external structure of the open aircraft hot air anti-icing of the present invention chamber experimental set-up.
Figure 1A is the exploded drawings of Fig. 1.
Fig. 2 is the constructional drawing of the anti-icing chamber of the present invention first plate 3.
Fig. 3 is the constructional drawing of the anti-icing chamber of the present invention second plate 4.
Fig. 4 is the exploded drawings of the conformal end-cap assembly of the present invention.
Fig. 4 A is the cut-away view of the conformal end-cap assembly of the present invention.
Fig. 4 B is the constructional drawing of nut in the conformal end-cap assembly of the present invention.
Fig. 5 is the constructional drawing of air feed bourdon's tube of the present invention.
Fig. 5 A is the circumferential section figure of air feed bourdon's tube of the present invention.
Fig. 5 B is the axial, cross-sectional view of air feed bourdon's tube of the present invention.
Fig. 5 C is the first of jet orifice in air feed bourdon's tube of the present invention schematic diagram of arranging.
Fig. 5 D is the second of jet orifice in air feed bourdon's tube of the present invention schematic diagram of arranging.
Fig. 5 E is the third schematic diagram of arranging of jet orifice in air feed bourdon's tube of the present invention.
Fig. 5 F is the constructional drawing that in air feed bourdon's tube of the present invention, jet orifice is cylindrical hole.
Fig. 5 G is the constructional drawing that in air feed bourdon's tube of the present invention, jet orifice is tapered through hole.
Fig. 6 is the assembly drowing of air feed bourdon's tube and aerofoil profile hot air anti-icing chamber cavity.
Fig. 6 A is that face figure is looked on the right side of air feed bourdon's tube together with the assembling of aerofoil profile hot air anti-icing chamber cavity.
The specific embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail.
Shown in Fig. 6, Fig. 6 A, aluminum aerofoil profile hot air anti-icing chamber cavity 1 is divided into the first wing chamber 11, the second wing chamber 12 by dividing plate 13 by cavity, between the anti-icing wall 17 of dividing plate 13 and cavity leading edge, leave gap 14, described gap is for being transferred to the second wing chamber 12 by the hot gas being entered by air feed bourdon's tube 2; The cavity of aerofoil profile hot air anti-icing chamber cavity 1 is provided with a plurality of deflation holes 15, and described deflation hole 15 is for discharging the hot gas in the second wing chamber 12.Air feed bourdon's tube 2 is placed in the first wing chamber 11, the high-pressure hot gas stream entering from air feed bourdon's tube 2 enters in the first wing chamber 11 by jet orifice 24 high speed jets, high speed thermal current in described the first wing chamber 11 is entered in the second wing chamber 12 by gap 14, by the deflation hole 15 on trailing edge wall 18, discharges.In order to disclose the influence factor of aerofoil profile hot air anti-icing chamber cavity 1 thermal behavior comprehensively, realization distributes known in the situation that at Anti-icing Heat Loads, can carry out the pre-designed of anti-icing chamber labyrinth and air feed parameter, and to known anti-icing chamber, can meet anti-icing demand and carry out science Evaluation on Total Performance efficiently.The invention discloses a kind of can be on aerofoil profile hot air anti-icing chamber cavity 1(also referred to as test specimen) labyrinth affect internal flow and pass the experimental set-up that thermal property is carried out in-depth study.
Shown in Fig. 1, Figure 1A, a kind of open aircraft hot air anti-icing chamber experimental set-up of the present invention's design, described experimental set-up includes air feed bourdon's tube 2, first anti-icing chamber plate the 3, second anti-icing chamber plate 4, the first packing ring 6, the second packing ring 7, conformal end-cap assembly 8, the fastening radius stay 51 of A, the fastening radius stay 52 of B, the fastening radius stay 53 of C and the fastening radius stay 54 of D.
The first packing ring 6 is identical with the structure of the second packing ring 7, and is the tangential dimensional airfoil structure in anti-icing chamber.
The structure of four fastening radius stays (being the fastening radius stay 51 of A, the fastening radius stay 52 of B, the fastening radius stay 53 of C, the fastening radius stay 54 of D) is identical, is metallic material.The two ends section of being threaded of fastening radius stay, the thread segment of one end is used for through the fourth hole 34 on the first anti-icing chamber plate 3, the thread segment of the other end is for through the fifth hole 46 on the second anti-icing chamber plate 4, then on thread segment, overlaps two ends that Upper gasket, nut just realized fastening radius stay fixing with first anti-icing chamber plate the 3 and second anti-icing chamber plate 4 respectively.Also will make aerofoil profile hot air anti-icing chamber cavity 1 be arranged between first anti-icing chamber plate the 3 and second anti-icing chamber plate 4 simultaneously.One end of four fastening radius stays is respectively through the through hole on first 3 four angles of anti-icing chamber plate, and the other end of four fastening radius stays is respectively through the through hole on second 4 four angles of anti-icing chamber plate.
(1) first anti-icing chamber plate 3
Shown in Fig. 1, Figure 1A, Fig. 2, the first anti-icing chamber plate 3 is provided with the first through hole 33 and fourth hole 34; In described the first through hole 33, be placed with the end cap seat 81 of conformal end-cap assembly 8; Described fourth hole 34 passes for one end of fastening radius stay.
The positive plate face 31 of the first anti-icing chamber plate 3 is provided with and wing the first identical wing groove 311 of aerofoil profile hot air anti-icing chamber cavity 1; Described the first wing groove 311 is for placing one end of aerofoil profile hot air anti-icing chamber cavity 1.The other end of aerofoil profile hot air anti-icing chamber cavity 1 is placed in the second wing groove 411 of the second anti-icing chamber plate 4.
The backboard face 32 of the first anti-icing chamber plate 3 is smooth plate face.
In the present invention, for the installation on the air feed bourdon's tube 2 of the realizing different structure not ally knock hole on the second anti-icing chamber plate 4, need to change the first anti-icing chamber plate 3 for knock hole described in each; The object of changing the first anti-icing chamber plate 3 is in order to guarantee that air feed bourdon's tube 2 keeps vertical and first anti-icing chamber plate the 3 and second anti-icing chamber plate 4 forever.Changing the first anti-icing chamber plate 3 is because the first through hole 33 positions that arrange on described the first anti-icing chamber plate 3 are different.Described air feed bourdon's tube 2 is forever vertical will guarantee the first through hole 33, knock hole, air feed bourdon's tube 2 concentrics exactly with first anti-icing chamber plate the 3 and second anti-icing chamber plate 4.
The first anti-icing chamber plate 3 is for the nonmetallic exhausted heat-insulating sheet material with high temperature resistant (300 degree are following) of some strength, as phenol aldehyde laminated cloth board, glass epoxy or high-temperature nylon plate.
(2) second anti-icing chamber plates 4
Shown in Fig. 1, Figure 1A, Fig. 3, the second anti-icing chamber plate 4 is provided with fifth hole 46; Described fifth hole 46 passes for the other end of fastening radius stay (51,52,53,54).
The second anti-icing chamber plate 4 positive plate face 41 be provided with and wing the second identical wing groove 411 of aerofoil profile hot air anti-icing chamber cavity 1; Described the second wing groove 411 is for placing the other end of aerofoil profile hot air anti-icing chamber cavity 1.
In described the second wing groove 411, be provided with a plurality of countersunk head knock holees (i.e. the first countersunk head knock hole 43, the second countersunk head knock hole 44, the 3rd countersunk head knock hole 45), described countersunk head knock hole is for placing the positioning end 21 of air feed bourdon's tube 2.A plurality of countersunk head knock holees is conducive to change air feed bourdon's tube 2 in the first cavity 11 positions of aerofoil profile hot air anti-icing chamber cavity 1.In the present invention, corresponding first anti-icing chamber plate 3, the second countersunk head knock holees 44 of the first countersunk head knock hole 43 by another anti-icing chamber of piece first plate 3, the three countersunk head knock holees 45 of correspondence by a correspondence first anti-icing chamber plate 3 again.Three blocks of described first anti-icing chamber plates 3 are because the position of the first through hole on the first anti-icing chamber plate 3 is different.
The second anti-icing chamber plate 4 is for the nonmetallic exhausted heat-insulating sheet material with high temperature resistant (300 degree are following) of some strength, as phenol aldehyde laminated cloth board, glass epoxy or high-temperature nylon plate.
In the present invention, a plurality of countersunk head knock holees (43,44,45) by design on the second anti-icing chamber plate 4 are installed the positioning end 21 of air feed bourdon's tube 2, thereby have realized first wing chamber 11Zhong position of air feed bourdon's tube 2 at aluminum aerofoil profile hot air anti-icing chamber cavity 1.Different positions needs the first corresponding different anti-icing chamber plates 3, thereby guarantees that air feed bourdon's tube 2 is forever perpendicular to first anti-icing chamber plate the 3 and second anti-icing chamber plate 4.By selecting different knock holees and corresponding the first anti-icing chamber plate 3, can realize the multiple relative mounting positions of bourdon's tube 2 and the anti-icing chamber of aerofoil profile cavity 1, in addition before screwing the nut 84 of conformal end-cap assembly 8, thereby can also change by rotation bourdon's tube 2 anti-icing wall 17 relative position relations of leading edge of jet orifices 24 and anti-icing chamber cavity 1.
(3) air feed bourdon's tube 2
Shown in Fig. 1, Figure 1A, Fig. 5, Fig. 5 B, air feed bourdon's tube 2 is hollow structure, and middle part is provided with blind hole 25; One end of air feed bourdon's tube 2 is positioning end 21, and the other end of air feed bourdon's tube 2 is inlet end 22.
The body 23 of air feed bourdon's tube 2 is provided with a plurality of jet orifices 24.
Air feed bourdon's tube 2 is metal tube, as stainless steel tube etc.
Shown in Fig. 5 A, air feed bourdon's tube 2 is provided with the jet orifice 24 that is no more than three row on circumference.Shown in Fig. 5 C, Fig. 5 D, Fig. 5 E, air feed bourdon's tube 2 can arrange a row jet orifice 24, also two row jet orifices 24 can be set on circumference, or three row jet orifices 24.Jet orifice 24 adopts the mode being intervally arranged, and can be that colleague's same column is arranged, and can be to be also staggered.Shown in Fig. 5 F, Fig. 5 G, the hole shape structure of jet orifice 24 can be cylindrical hole (being borehole structure), can be also conical through-hole (being convergent pore structure), and the bore dia of jet orifice 24 is designated as d, and this diameter refers to the diameter at the minimum place of jet orifice 24.
Shown in Fig. 5 B, the axial distribution of air feed bourdon's tube 2 can find out that its center is blind hole 25.
In the present invention, in order to study anti-icing part of anti-icing leading edge cavity and average wall coefficient of heat transmission (Nusselt number) with the air feed of air feed bourdon's tube 2 and the variation relation of geometric parameter, on air feed bourdon's tube 2, structure, jet orifice 24 arrangement modes and the air feed bourdon's tube 2 of the jet orifice 24 of design relative position and satisfied the closing of hot air anti-icing chamber internal flow heat transfer factor in aluminum aerofoil profile hot air anti-icing chamber cavity 1 is
re represents air feed Reynolds number, and Pr represents Prandtl number, X
nrepresent jet orifice 24 interval in the axial direction, Y
nrepresent the arc length interval of jet orifice 24 on circumference, d represents the diameter of jet orifice 24, and D represents the outer tube diameter of bourdon's tube 2, and H represents that leading edge stationary point 16 is to the distance of bourdon's tube 2 center-points, Z
nrepresent that leading edge stationary point 16 is to the spacing of bourdon's tube 2 outside faces, and
In the present invention, the conformal end-cap assembly 8 that the outer tube diameter of selection and air feed bourdon's tube 2 matches, one end of bourdon's tube 2 is through the second through hole 843, the interior placement silicon rubber loop of groove 815 (being large sealing packing ring 82) at dish edge 814, the first anti-icing chamber plate 3 and end cap seat 81 screw threads are installed, packing ring 85 and small sealing ring 83 are inserted on the Internal baffle 842 of nut 84, on the thread segment of end cap 8, be socketed upper cap nut 84.On bourdon's tube 2, being inserted in successively described in nut 84(nut 84 can fastening bourdon's tube) and tetrafluoro packing ring 85, and through the first through hole 33 on the first anti-icing chamber plate 3, the positioning end of bourdon's tube 2 is inserted in the knock hole (43,44,45) of the second anti-icing chamber plate 4, rotation regulates bourdon's tube 2 until jet orifice 24 is correct with the relative position of the leading edge wall of aerofoil profile hot air anti-icing chamber cavity 1, screw bourdon's tube fastening nut 84, complete the installation of bourdon's tube 2.
(4) conformal end-cap assembly 8
Shown in Fig. 1, Figure 1A, Fig. 4, Fig. 4 A, conformal end-cap assembly 8 includes end cap seat 81, large sealing packing ring 82, small sealing ring 83, nut 84 and packing ring 85;
Described end cap Zuo81 center offers third through-hole 812, and the outside of described end cap seat 81 is provided with dish edge 814; Dish edge 814 is provided with groove 815(groove 815 for placing large sealing packing ring 82) and tapped bore 816 is installed; One end of described end cap seat 81 is external thread section 811, and the other end of described end cap seat 81 is smooth section 813.The nut 84 that has been threaded on the external thread section 811 of described end cap seat 81 when nut 84 is installed with end cap seat 81, is first put into after packing ring 85, small sealing ring 83 in nut 84, nut 84 is enclosed within on the external thread section 811 of end cap seat 81.
Shown in Fig. 4 B, described nut 84 centers are second through holes 843, in described the second through hole 843, are provided with negative thread 841 and Internal baffle 842, and described Internal baffle 842 is for placing packing ring 85.When nut 84 is installed with end cap seat 81, first in nut 84, put into after packing ring 85, small sealing ring 83, nut 84 is enclosed within on the external thread section 811 of end cap seat 81.
The installation of conformal end-cap assembly 8 and the first anti-icing chamber plate 3: first the smooth section of end cap seat 81 813 is passed after the first through hole 33 of the first anti-icing chamber plate 3, then at the interior placement large sealing packing ring 82 of groove 815, by after the interior placement packing ring 85 of nut 84 and small sealing ring 83, nut 84 is connected to the thread segment 811 of end cap seat 81 again.By large small sealing ring, realized conformal end-cap assembly 8 and the first anti-icing chamber plate 3 is tightly connected.
A kind of open aircraft hot air anti-icing chamber experimental set-up of the present invention's design, the assembly relation of its parts is: the positioning end 21 of conformal bourdon's tube 2 is arranged on the countersunk head knock hole (43 of the second anti-icing chamber plate 4, 44, 45) in, tangential dimensional airfoil the second packing ring 7 in anti-icing chamber is placed in to the second wing groove 411 of the second anti-icing chamber plate 4, tangential dimensional airfoil the first packing ring 6 in anti-icing chamber is placed in to the first wing groove 311 of the first anti-icing chamber plate 3, end cap seat 81 in conformal end-cap assembly 8 is arranged in the first through hole 33 of the first anti-icing chamber plate 3, the two ends of test specimen (aluminum aerofoil profile hot air anti-icing chamber cavity 1) are arranged on respectively between first anti-icing chamber plate the 3 and second anti-icing chamber plate 4, to on the thread segment of the end cap seat 81 in conformal end-cap assembly 8, connect upper cap nut, the distance of regulating nut and thread segment clamps test specimen between first anti-icing chamber plate the 3 and second anti-icing chamber plate 4, then 4 fastening radius stays (51,52,53,54) are passed to the corresponding mounting hole of first anti-icing chamber plate the 3 and second anti-icing chamber plate 4, by realizing the installation that clamps test specimen (aluminum aerofoil profile hot air anti-icing chamber cavity 1) behind fastening nuts radius stay two ends.
A kind of open aircraft hot air anti-icing chamber experimental set-up of the present invention's design, can realize fast test specimen is combined with the bourdon's tube of various structures, and change the relative position of bourdon's tube in test specimen cavity, make can accurately pay close attention in the test of hot air anti-icing chamber internal flow heat transfer characteristic, with each the ad hoc structure parameter effect in jet flow in the hot air anti-icing chamber of bourdon's tube array jetting, and how to affect the heat exchange on cavity wall, this instructs the design of hot air anti-icing cavity configuration by helping and optimizes distribution and the Rational choice of air feed parameter, for design and the performance evaluation of high efficiency hot gas anti icing system provides foundation.
Claims (9)
1. an open aircraft hot air anti-icing chamber experimental set-up, is characterized in that: include air feed bourdon's tube (2), the first anti-icing chamber plate (3), the second anti-icing chamber plate (4), the first packing ring (6), the second packing ring (7), conformal end-cap assembly (8) and fastening radius stay; Fastening radius stay is arranged between the first anti-icing chamber plate (3) and the second anti-icing chamber plate (4);
The first anti-icing chamber plate (3) is provided with the first through hole (33) and fourth hole (34); In described the first through hole (33), be placed with the end cap seat (81) of conformal end-cap assembly (8); Described fourth hole (34) passes for one end of fastening radius stay;
The positive plate face (31) of the first anti-icing chamber plate (3) is provided with and wing the first identical wing groove (311) of aerofoil profile hot air anti-icing chamber cavity (1); Described the first wing groove (311) is for placing one end of aerofoil profile hot air anti-icing chamber cavity (1);
The second anti-icing chamber plate (4) is provided with fifth hole (46); Described fifth hole (46) passes for the other end of fastening radius stay;
The positive plate face (41) of the second anti-icing chamber plate (4) is provided with and wing the second identical wing groove (411) of aerofoil profile hot air anti-icing chamber cavity (1); Described the second wing groove (411) is for placing the other end of aerofoil profile hot air anti-icing chamber cavity (1); In described the second wing groove (411), be provided with countersunk head knock hole, described countersunk head knock hole is used for placing the positioning end (21) of air feed bourdon's tube (2);
Air feed bourdon's tube (2) is hollow structure, and middle part is provided with blind hole (25); One end of air feed bourdon's tube (2) is positioning end (21), and the other end of air feed bourdon's tube (2) is inlet end (22); The body (23) of air feed bourdon's tube (2) is provided with a plurality of jet orifices (24);
Conformal end-cap assembly (8) includes end cap seat (81), large sealing packing ring (82), small sealing ring (83), nut (84) and packing ring (85); The center of described end cap seat (81) offers third through-hole (812), and the outside of described end cap seat (81) is provided with dish edge (814); Dish edge (814) is provided with groove (815) and tapped bore (816) is installed, and described groove (815) is for placing large sealing packing ring (82); One end of described end cap seat (81) is external thread section (811), and the other end of described end cap seat (81) is smooth section (813); Nut (84) has been threaded on the external thread section (811) of described end cap seat (81), when nut (84) is installed with end cap seat (81), first in nut (84), put into after packing ring (85), small sealing ring (83), nut (84) is enclosed within on the external thread section (811) of end cap seat (81);
Described nut (84) center is the second through hole (843), is provided with negative thread (841) and Internal baffle (842) in described the second through hole (843), and described Internal baffle (842) is for placing packing ring (85).
2. open aircraft hot air anti-icing according to claim 1 chamber experimental set-up, is characterized in that: air feed bourdon's tube (2) is provided with the jet orifice (24) that is no more than three row on circumference.
3. open aircraft hot air anti-icing according to claim 1 chamber experimental set-up, is characterized in that: the jet orifice (24) on air feed bourdon's tube (2) is manhole.
4. open aircraft hot air anti-icing according to claim 1 chamber experimental set-up, is characterized in that: the jet orifice (24) on air feed bourdon's tube (2) is conical through-hole.
5. open aircraft hot air anti-icing according to claim 1 chamber experimental set-up, is characterized in that: the arranging in the axial direction of the jet orifice (24) on air feed bourdon's tube (2) arranged for colleague's same column.
6. open aircraft hot air anti-icing according to claim 1 chamber experimental set-up, is characterized in that: the arranging as being staggered in the axial direction of the jet orifice (24) on air feed bourdon's tube (2).
7. open aircraft hot air anti-icing according to claim 1 chamber experimental set-up, it is characterized in that: the air feed bourdon's tube (2) of realizing different structure by changing the first anti-icing chamber plate (3) is changed, guarantee that air feed bourdon's tube (2) is perpendicular to the first anti-icing chamber plate (3) and the second anti-icing chamber plate (4) simultaneously.
8. open aircraft hot air anti-icing according to claim 1 chamber experimental set-up, it is characterized in that: the positioning end of air feed bourdon's tube (2) coordinates with a plurality of countersunk head knock holees on the second anti-icing chamber plate (4), realized the position of air feed bourdon's tube (2) in aerofoil profile hot air anti-icing chamber cavity (1) and changed.
9. open aircraft hot air anti-icing according to claim 1 chamber experimental set-up, is characterized in that: the first anti-icing chamber plate (3) and the second anti-icing chamber plate (4) are exhausted heat-insulating sheet material.
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| CN201210236602.8A CN102756809B (en) | 2012-07-07 | 2012-07-07 | Opened type airplane hot-gas anti-icing test device |
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| CN201210236602.8A CN102756809B (en) | 2012-07-07 | 2012-07-07 | Opened type airplane hot-gas anti-icing test device |
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| CN102756809B true CN102756809B (en) | 2014-05-07 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3196123A1 (en) * | 2016-01-21 | 2017-07-26 | Mitsubishi Aircraft Corporation | Anti-icing system and aircraft |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103076150B (en) * | 2012-11-28 | 2015-08-05 | 中国商用飞机有限责任公司 | A kind of Wing-type test piece |
| CN103017998A (en) * | 2012-11-28 | 2013-04-03 | 中国商用飞机有限责任公司 | Wing-type test piece |
| CN105699044B (en) * | 2016-04-20 | 2019-03-26 | 上海交通大学 | The icing mnncl tcst device of aero-engine air intake duct supporting plate |
| CN107128510B (en) * | 2017-05-22 | 2019-11-05 | 北京航空航天大学 | A kind of lifting airscrew is anti-/ deicing experiment porch |
| CN110789729B (en) * | 2018-08-02 | 2024-01-30 | 中国商用飞机有限责任公司 | Guide tool and replacement method for flute-shaped pipe of aircraft slat |
| CN112556728B (en) * | 2019-09-25 | 2022-07-19 | 中国航发商用航空发动机有限责任公司 | Anti-icing sensor and have its engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3917193A (en) * | 1974-01-21 | 1975-11-04 | Boeing Co | Boundary layer control and anti-icing apparatus for an aircraft wing |
| BR8602400A (en) * | 1985-06-03 | 1987-01-21 | Short Brothers Plc | HOT AIR DUCT |
| EP0376371A2 (en) * | 1988-12-30 | 1990-07-04 | The Boeing Company | Thermal anti-icing system for aircraft |
| CN101813589A (en) * | 2009-03-18 | 2010-08-25 | 洛阳轴研科技股份有限公司 | Reliable test method of anti-icing telescopic pipe bearing for aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8100364B2 (en) * | 2009-01-15 | 2012-01-24 | Textron Innovations Inc. | Anti-icing piccolo tube standoff |
-
2012
- 2012-07-07 CN CN201210236602.8A patent/CN102756809B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3917193A (en) * | 1974-01-21 | 1975-11-04 | Boeing Co | Boundary layer control and anti-icing apparatus for an aircraft wing |
| BR8602400A (en) * | 1985-06-03 | 1987-01-21 | Short Brothers Plc | HOT AIR DUCT |
| EP0376371A2 (en) * | 1988-12-30 | 1990-07-04 | The Boeing Company | Thermal anti-icing system for aircraft |
| CN101813589A (en) * | 2009-03-18 | 2010-08-25 | 洛阳轴研科技股份有限公司 | Reliable test method of anti-icing telescopic pipe bearing for aircraft |
Non-Patent Citations (2)
| Title |
|---|
| M.IMBRIALE etc..VISUALIZATION OF THE HEAT TRANSFER ON A WING LEADING EDGE SURFACE INTERNALLY IMPINGED BY A ROW OR AIR JETS.《15th International Symposium on Flow Visualization》.2012, |
| VISUALIZATION OF THE HEAT TRANSFER ON A WING LEADING EDGE SURFACE INTERNALLY IMPINGED BY A ROW OR AIR JETS;M.IMBRIALE etc.;《15th International Symposium on Flow Visualization》;20120628;1-10 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3196123A1 (en) * | 2016-01-21 | 2017-07-26 | Mitsubishi Aircraft Corporation | Anti-icing system and aircraft |
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