WO1990009243A1 - Tuyere supersonique attenuant le bruit - Google Patents

Tuyere supersonique attenuant le bruit Download PDF

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Publication number
WO1990009243A1
WO1990009243A1 PCT/US1990/000688 US9000688W WO9009243A1 WO 1990009243 A1 WO1990009243 A1 WO 1990009243A1 US 9000688 W US9000688 W US 9000688W WO 9009243 A1 WO9009243 A1 WO 9009243A1
Authority
WO
WIPO (PCT)
Prior art keywords
nozzle
supersonic
exit
passageway
inlet
Prior art date
Application number
PCT/US1990/000688
Other languages
English (en)
Inventor
Daniel L. Lloyd
Richard J. Madlener
Original Assignee
Cold Jet, Inc.
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Cold Jet, Inc. filed Critical Cold Jet, Inc.
Priority to EP90904011A priority Critical patent/EP0414863B1/fr
Priority to DE69011014T priority patent/DE69011014T2/de
Publication of WO1990009243A1 publication Critical patent/WO1990009243A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C5/00—Devices or accessories for generating abrasive blasts
    • B24C5/02—Blast guns, e.g. for generating high velocity abrasive fluid jets for cutting materials
    • B24C5/04—Nozzles therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B1/00—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means
    • B05B1/002—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to reduce the generation or the transmission of noise or to produce a particular sound; associated with noise monitoring means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/003—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods using material which dissolves or changes phase after the treatment, e.g. ice, CO2

Definitions

  • the present invention relates generally to supersonic nozzles and is particularly directed to attenuating the noise emitted by supersonic nozzles during operation.
  • the invention will be specifically disclosed in connection with a supersonic nozzle having an exit to throat ratio within a specified range, internal features of the supersonic passageway, and external configurations of the nozzle 5 body which tend to reduce the noise emitted therefrom.
  • Supersonic nozzles are well known in the art.
  • Conventional converging-diverging nozzles include a converging section, a throat, and a diverging 0 section. If sufficient pressure is applied to a converging-diverging nozzle, air velocity of the throat will become sonic, and then increase as the air expands at the diverging section to produce a supersonic outlet velocity. The exact exit velocity 5 depends on air pressure, size, and other details of the nozzle design.
  • Nozzles may be used for a variety of purposes. They may be operated automatically while located a distance from the operator and other people. Other Q nozzles may be hand held by an operator who directs the exiting flow in order to achieve a particular purpose. One specific use of such nozzles is in combination with a particle blast cleaning apparatus such as that disclosed in U.S. Patent No. 4,744,181.
  • Such nozzles are typically of the type hand held by an operator, who directs the flow, which is a mixture of transport gas flowing at a supersonic velocity and carbon dioxide pellets carried along by the transport gas.
  • the flow is directed onto an object to be cleaned by particle blast or cryogenic particle blast cleaning methods.
  • a major problem with the use of supersonic nozzles is the decibel level of the noise emitted by the nozzle during operation. Such noise becomes a critical factor in the acceptability and use of a particular nozzle design when people are required to be nearby. Furthermore, when such nozzles are used in an enclosed area, such as a factory, the reflective surfaces of the area can tend to increase the decibel level experienced at particular locations.
  • a sound pressure level of 120 dB on the A scale (dBA) has been determined by OSHA to be the threshold level of pain for a human being. However, in occupational situations, OSHA limits the exposure level of a person to such noises to less than 90 dBA for an eight hour time period. Industry and military standards establish this level at 85 dBA.
  • Typical prior art nozzles as used for particle blast cleaning apparatuses, have been measured to emit noise as high as 130 dBA at the operator's position.
  • the nozzle disclosed by U.S. Patent No. 4,038,786 has been documented to emit noise in the range of 127 dBA. Since the dB scale is logarithymic, a change of three decibels represents a doubling of the sound pressure level.
  • the difference between the OSHA 120 dBA threshold level of pain and the 127 dBA of the typical prior art nozzle represents over a fourfold increase in the sound pressure level. When compared to the 90 dBA OSHA limit, this difference is an increase of over 4,000 times the sound pressure level of 90 dBA.
  • the 127 dBA level of the typical prior art nozzle has a sound pressure level more than 16,000 times this standard.
  • the sound emitted by supersonic nozzles must be reduced to as low a level as possible to permit safe continuous operation. While ear protection is available, such protective devices attenuate the noise only in the range of 20 to 25 dBA. This would result in a sound pressure level of the typical 127 dBA prior art nozzle of as low as a 102 dBA at the operator's position. While this would drastically reduce the sound pressure level experienced by the operator, it would still remain above the OSHA, industry, and military limits for eight hours of exposure. Furthermore, in a factory situation, it is unrealistic to require workers in nearby areas who are not involved with the supersonic nozzle use to wear such ear protection.
  • the ultimate goal and solution is to use a supersonic nozzle which has a sound pressure level low enough that an operator wearing approved ear protection devices is subjected to less than 85 dBA. Such a nozzle would have to have a sound pressure level of less than 115 dBA at the operator position. The 115 dBA level would also be acceptable to workers without ear protection devices who are more than 15 feet from the operating nozzle.
  • an improved supersonic nozzle which has a passageway formed in a nozzle body which has an inlet, a throat, and an exit.
  • the exit area to throat area ratio is in the range of 2.5 to 6.0 whereby the static pressure of the supersonic flow at the exit is less than the static ambient pressure.
  • a plurality of longitudinal grooves are formed adjacent the interior wall of the supersonic passageway and adjacent the exit. According to a further aspect of the invention, the grooves extend from exit inwardly towards the throat to the point along the length of the passageway at which the static pressure of the flow is equal to the static ambient pressure.
  • the supersonic passageway has an elongated rectangular cross section which is formed by two sets of opposing surfaces and the longitudinal grooves are formed in one set of the opposing surfaces.
  • a nozzle inlet is connected to the nozzle body which has an inlet passageway which delivers the flow of compressible fluid to the supersonic passageway.
  • the inlet passageway has a circular cross section at its inlet and a rectangular cross section at its outlet.
  • a plurality of cavities are formed in the exterior surface of the nozzle body.
  • the cavities may be filled with a plurality of inserts that are composed of a dissimilar material.
  • the cavities are formed longitudinally in the exterior surface of the nozzle body, and may be filled with inserts made of a metal which has a greater density than the material from which the nozzle body is formed.
  • the supersonic passageway of the nozzle has an exit area to throat area ratio in the range of 2.5 to 6.0, and - 6 -
  • nozzle body also has a plurality of longitudinal ribs formed in the supersonic passageway, as well as a plurality of inserts disposed in a plurality of longitudinal cavities formed in the exterior surface of the nozzle body.
  • a shield is disposed about the exterior surface of the nozzle body and extends in the direction of flow beyond the exit, forming an exit opening which is aligned with the exit of the supersonic passageway.
  • the exit opening has a cross sectional area at least as large as the cross sectional area of the exit of the supersonic passageway.
  • the exit opening is at least 25% larger than the exit opening of the supersonic passageway.
  • means are provided for allowing auxiliary air flow into the exit cavity, with the auxiliary air flow exiting through the exit opening.
  • a gill cavity is formed between the exterior surface of the nozzle body and the shield.
  • the angle formed between the exterior surface of the nozzle body and the perimeter of the exit opening is at least 60°.
  • the shield does not directly contact any portion of the exterior surface of the nozzle body.
  • Figure 1 is a perspective view of a first embodiment of the supersonic nozzle.
  • Figure 2 is an end view along line A of figure 1 showing the exit of the supersonic nozzle.
  • Figure 3 is a cross sectional view taken along line 3-3 of figure 2 showing the supersonic passageway and its profile, as well as longitudinal ribs formed adjacent the exit of the supersonic passageway.
  • Figure 4 is a cross sectional view of the throat of the supersonic passageway taken along lines 3-3 of figure 3, showing in phantom lines the mating portion of the nozzle body.
  • Figure 5 is a perspective view of a second, embodiment of the supersonic nozzle having longitudinal inserts disposed in longitudinal cavities formed in the exterior surface of the nozzle body.
  • Figure 6 is a perspective view of a third embodiment of the supersonic nozzle having a shield - 8 -
  • nozzle body disposed about the exterior surface of the nozzle body.
  • Figure 7 is an exploded perspective view of the supersonic nozzle and shield of figure 6.
  • Figure 8 is a side elevational view of a portion of the shield of figure 6.
  • Figure 9 is an end elevational view of the shield of figure 8.
  • Figure 10 is a top view of a portion of the shield of figure 6.
  • Figure 11 is a side elevational view with the shield shown in partial cross section showing the nozzle and shield assembly of figure 6.
  • Figure 12 is an end view of the nozzle of figure 6 in partial cross section showing the exit opening and the nozzle exit.
  • Figure 13 is a perspective view showing a fourth embodiment of the supersonic nozzle.
  • Figure 14 is a perspective view of a fifth embodiment showing a supersonic nozzle having a circular exit.
  • figure 1 shows a supersonic nozzle generally designated by the numeral 1 constructed in accordance with the present invention.
  • Nozzle body 2 is shown as being formed of an upper section 3 and a lower section 4, held together by a plurality of fasteners, such as bolts 5.
  • the supersonic passageway 6 is formed symmetrically in upper section 3 and lower section 4, and is shown as a profile.
  • nozzle inlet 10 is shown connected to nozzle body 2 by bolts 11.
  • a passageway (not shown) is formed through the interior of nozzle inlet 10 which communicates with inlet 7 at one end, and is connectable to receive a flow of compressible fluid at the other end 12.
  • a pair of spaced grooves 13, 14 are formed about the circumference of nozzle inlet 10 near end 12.
  • Passageway 6 and exit 9 are shown as having an elongated rectangular cross sectional shape. In principle, as depicted here, an elongated rectangle has a dimension in one direction which is substantially larger than the dimension in the other direction.
  • the rectangle is formed by an interior wall 16 of supersonic passageway 6. While supersonic passageway 6 is shown as an elongated rectangle in cross section, as will be described later, it may also be circular in cross section. With either shape, an elongated rectangle or a circle, supersonic passageway 6 is considered to have one interior wall 16, although as shown in figure 2 with the elongated rectangular cross sectional shape, there are four distinct surfaces, 16A, 16B, 16C, and 16D. As shown, the rectangular cross section can be considered to be constructed of two sets of opposing surfaces 16A-16C, and 16B-16D.
  • grooves 17 are shown adjacent exit 9 in figure 3, as actually starting at exit 9. In practice, grooves 17 may actually extend from exit 9, or be - 10 -
  • grooves 17 extend inwardly from exit 9 toward throat 8 along a length of supersonic passageway 6, to point 18. As shown, grooves 17 are formed as a series of recesses 17A and ridges 17B, along interior walls 16B and 16D.
  • supersonic passageway 6 is shown having a converging section 19 from inlet 7 to throat 8.
  • a diverging section 19A is shown from throat 8 to exit 9.
  • Figure 4 shows a cross section taken through throat 8, showing the rectangular shape thereof, and also indicating that throat 8 has the smallest cross sectional area of any location in supersonic passageway 6.
  • end 12 of nozzle inlet 10 is connected to flexible hose (not shown) which delivers a continuous flow of a compressible fluid.
  • compressible fluids are gases and may be accelerated to supersonic flow through a converging-diverging nozzle.
  • Grooves 13 and 14 are adapted to be received by a quick disconnect mechanism (not shown) attached to the hose delivering the flow of compressible fluid.
  • the interior cavity (not shown) of nozzle inlet 10 changes from a circular cross section to a rectangular cross section along the length of nozzle inlet 10 to where it is delivered into inlet 7 of supersonic passageway 6.
  • the sonic flow following well known laws of physics, is accelerated to a supersonic velocity as it flows through diverging section 19A and leaves the nozzle 1 through exit 9.
  • the static pressure of the flow at the exit will be equal to 0 psig, or stated another way, will be equal to the static ambient pressure.
  • a nozzle which has a lower static pressure at exit 9 is referred to as an overexpanded - underdeveloped nozzle. In such an overexpanded nozzle, the static pressure of the flow reaches 0 psig at a point upstream of the exit. This reduces the efficiency of the nozzle in terms of maximizing the momentum of the flow exiting the nozzle.
  • shock waves form in such supersonic flow as present here at the point at which the static pressure of the flow is equal to 0 psig.
  • shock waves are formed externally at the exit, and travel from the supersonic passageway. It is these shock waves which produce the high sound pressure level of a supersonic nozzle while it is operating.
  • the present embodiment of the invention lowers the noise generated by the supersonic nozzle 1 by overexpanding the nozzle.
  • the flow through the supersonic nozzle 1 reaches 0 psig static pressure at location 18. It is at this point in supersonic passageway 6 that shock waves form.
  • the shock waves are attenuated as they travel from location 19 through exit 9 and out to the ambient environment.
  • the noise level is reduced by this design.
  • exit to throat ratio is the ratio of the cross sectional area of exit 9 to the cross sectional area of throat 8.
  • isentropic flow no losses
  • the ratio of 2.77 theoretically achieves 0 psig static pressure at the exit.
  • ideal flow no losses
  • the actual ratio which produces 0 psig static pressure is in fact less than 2.77.
  • an exit to throat ratio of 2.48 will produce a static pressure of 0 psig at the exit.
  • an exit to throat ratio of greater than 2.5 is necessary.
  • another embodiment of the present invention also includes grooves 17 formed in the exterior wall 16 of supersonic passageway 6 as described above. The location of these grooves 17 near exit 9 of supersonic passageway 6, assists in preventing the shock waves from coalescing with one another and thereby enhancing and re-enforcing themselves.
  • Grooves 17 are shown as extending upstream from exit 9 to the point along the length of supersonic passageway 6 at which 0 psig static pressure occurs in the flow. If grooves 17 were to extend beyond this point, there would be some loss in efficiency of the nozzle without any corresponding gain in sound attenuation. This is because the shock waves are not formed upstream of location 18, and, therefore, any portion of grooves 17 extending beyond location 18 will not be functional with respect to preventing the coalescing of shock waves. As shown in figure 2, grooves 17 are formed in interior wall 16, and in particular, on one set of opposing surfaces 16B, 16D. This embodiment operates efficiently when the distance between the grooves 17 from ridge to ridge 17B is .030 inches to .050 inches.
  • the depth of grooves 17 from ridge 17B to recess 17A is in the range of .005 inches to .015 inches. If the grooves 17 are too shallow, the grooves 17 are ineffective in preventing the coalescing of shock waves. If the grooves 17 are too deep, they reduce the efficiency of the nozzle.
  • supersonic nozzle 1 having a plurality of inserts 20 complimentary in shape to and disposed in longitudinal cavities 20A formed in exterior surface 15. As indicated, in the present embodiment, inserts 20 are disposed. ⁇ on opposite exterior surfaces 15B and 15D. Inserts 20 and cavities 20A are shown as running the length of nozzle body 2, terminating at end 21 of nozzle body 2. Inserts 20 may be flush with exterior surface 15 as shown or may terminate above or below exterior surface 15. Inserts 20 may be a single piece per cavity 20A or may be layered of several inserts 20 in one cavity 20A.
  • nozzle body 2 may be formed of any suitable material, in the present embodiment it is formed of aluminum. Inserts 20 are preferably of a similar material, having a greater density than the -material which forms nozzle body 2. In the present embodiment, inserts 20 are made of lead. Noise generated by the operation of supersonic nozzle 1 may also travel through nozzle body 2, being absorbed and then re-emitted from the nozzle. By disposing inserts 20 in cavities 20A on exterior surface 15 of nozzle body 2, the ability of nozzle body 2 to transmit the noise is reduced. By forming discontinuous shapes, i.e. cavities 20A, in exterior surface 15, resonance in surface 15 is prevented at certain frequencies. Inserts 20 formed of lead, absorb some of the energy of the transmitted sound due to the density of the lead, and thereby reduces the transmission of sound from the surface of the lead.
  • FIG 5 An alternative embodiment to figure 5, is to form cavities 20A in exterior surface 15 of nozzle body 2 without disposing inserts in cavities 20A. As mentioned above, such discontinuity of exterior surface 15 helps to decrease the transmission of sound therefrom. However, also as described, the sound is reduced even further by filling cavities 20A with inserts 20. Although longitudinal cavities and inserts are shown, randomly sized and located cavities and inserts will also produce similar sound attenuation. Although figure 5 shows the use of cavities 20A and inserts 20 on a nozzle having grooves 17 in supersonic passageway 6, it should be understood that either may be used alone or in combination.
  • Supersonic nozzle 1 has a shield 22 disposed about a portion of exterior surface 15 of nozzle body 2.
  • the shield is formed of two portions, 22A, 22B, and is secured by a plurality of bolts 23 which also hold upper section 3 and lower section 4 of nozzle body 2 together.
  • Shield 22 is shown - 15 -
  • Exit opening 24 is formed at end 25 of shield 22. Exit opening 24 is defined by perimeter 26 and is generally aligned with exit 9 as shown in figure 12.
  • Exit opening 24 is larger than exit 9, and as shown, is preferably at least 25% larger than exit 9.
  • FIG 8 shows a side elevational view of shield portion 22B.
  • shield 22B has sides 27A and 27B extending perpendicularly
  • symmetrical shields 22A and 22B are assembled about nozzle body 2, with spacers 33 located between exterior surface 15 and steps 30A and 30B, thereby preventing any direct contact between shield 22 and nozzle body 2.
  • distance between sides 27A and 27B is greater than the distance between exterior surfaces ISA and 15C, also preventing any direct contact between shield 22 and nozzle body 2.
  • Exit cavity 34 is defined by exit 9 of supersonic passageway 6, shield 22A, 22B, and exit opening 24.
  • Exit cavity 34 is defined by exit 9 of supersonic passageway 6, shield 22A, 22B, and exit opening 24.
  • Formed between shield 22 and exterior surface 15 is an air cavity or gill cavity
  • gill cavity 35 which communicates with the ambient environment at gill opening 36 at one end, and with exit cavity 34 at the other end.
  • the size of gill cavity 35 is further enhanced by the spacing of shield 22A, 22B from exterior surface 15 by a plurality of spacers
  • shield 22 By assembling shield 22 to surround nozzle body 2 as shown in figures 6, 11, and 12, additional sound attenuation is achieved.
  • the transmission of sound from exterior surface 15 of nozzle body 2 is reduced due to the spacing of shield 22A, 22B from exterior surface 15. Sound which reaches shield 22A, 22B is reflected and absorbed by the interior surface 37A of shield 22 and only a portion of the sound is re-emitted from the exterior surface 37 of shield 22.
  • exit cavity 34 acts to attenuate the shock waves emerging with the flow from exit 9 prior to exiting through exit opening 24.
  • exit opening 24 It is important that exit opening 24 not act as the exit of supersonic nozzle 1. To prevent this, an auxiliary air flow passes through gill cavity 35, and exits through exit opening 24 in combination with the supersonic flow from exit 9.
  • the supply of auxiliary air through gill cavity 27 must be sufficient to prevent any effect of exit cavity 34 on the actual supersonic flow at exit 9. Satisfactory auxiliary air flow has been achieved in practice by maintaining the depth of relief 29 formed in shield 22A and 22B at .050 inches.
  • the auxiliary air flow mixes with the supersonic air flow while exiting through exit opening 24. To prevent turbulence and other undesirable effects, it is best if the mixing of the two flows occurs as tangentially as possible. To this end, it has been determined that optimum results are obtained if the angle 38 formed between exterior surface 15 at end 39 of nozzle body 2 and perimeter 26 be no less than 60°, although the nozzle 1 is operable with an angle 38 of less than 60°. Angle 38 is called the gill angle. It is anticipated that the nozzle body will be formed of aluminum. Shield 22 may be formed of brass or other similar material. Spacers 33 are formed of a fiber material, having poor sound transmission properties, to reduce the transmission of sound from exterior surface 15 through spacers 33 to shield 22.
  • shield 22 be used in combination with grooves 17 and a supersonic nozzle having an exit to throat ratio in the range of 2.5 to 6.0, the shield will in fact attenuate sound independent of the presence of grooves 17.
  • the preferred embodiment encompasses all three of these features. Additionally, one skilled in the art may find improvement in the sound attenuation performance of the preferred embodiment by further disposing cavities and inserts (not shown) on exterior surface 37 of shield 22.
  • Figure 12 shows an end view of the nozzle of figure 6, with shield 22 partially cut away. As can be seen, exit opening 24 is aligned with exit 9. Gill cavity 35 extends completely around nozzle body 2 between exterior surface 15 and interior surface 37A of shield 22.
  • the inventors have determined that a nozzle according to the present invention, having an exit to throat ratio of 2.69 in combination with grooves formed in the supersonic passageway as described above, will produce a sound pressure level of 112 dBA at the operator position. By adding the shield to this nozzle, further sound attenuation is achieved and the sound pressure level at the operator's location is reduced to as low as 104 dBA.
  • Figure 13 shows another embodiment of the present invention having an elongated nozzle body 40, with shield 41 secured near the end of the nozzle body 40 as described above in conjunction with the embodiment of figure 6.
  • Figure 14 shows another embodiment having a supersonic passageway with a circular cross section in combination with grooves formed in the interior wall of the supersonic passageway, and a shield disposed about the nozzle body, spaced therefrom.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Nozzles (AREA)
  • Percussion Or Vibration Massage (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • On-Site Construction Work That Accompanies The Preparation And Application Of Concrete (AREA)
  • Aeration Devices For Treatment Of Activated Polluted Sludge (AREA)

Abstract

Une tuyère supersonique (1) atténuant le bruit a un rapport entre la sortie (9) et l'étranglement (8) situé dans la plage comprise entre 2,5 et 6,0, des gorges longitudinales (17) étant formées dans la paroi intérieure du passage supersonique (6) du corps (2) de l'ajutage. Un écran de protection est disposé autour de la surface extérieure du corps de l'ajutage, formant une cavité de sortie ainsi qu'une ouverture de sortie, et comporte une cavité à ailettes à travers laquelle de l'air auxiliaire s'écoule jusque dans la cavité de sortie et se mélange au flux supersonique.
PCT/US1990/000688 1989-02-08 1990-02-07 Tuyere supersonique attenuant le bruit WO1990009243A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP90904011A EP0414863B1 (fr) 1989-02-08 1990-02-07 Tuyere supersonique attenuant le bruit
DE69011014T DE69011014T2 (de) 1989-02-08 1990-02-07 Überschalldüse mit reduziertem geräusch.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US30817389A 1989-02-08 1989-02-08
US308,173 1989-02-08

Publications (1)

Publication Number Publication Date
WO1990009243A1 true WO1990009243A1 (fr) 1990-08-23

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ID=23192867

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1990/000688 WO1990009243A1 (fr) 1989-02-08 1990-02-07 Tuyere supersonique attenuant le bruit

Country Status (5)

Country Link
EP (1) EP0414863B1 (fr)
JP (1) JPH03504824A (fr)
AT (1) ATE109030T1 (fr)
DE (1) DE69011014T2 (fr)
WO (1) WO1990009243A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996007050A1 (fr) * 1994-08-30 1996-03-07 Bosch Systemes De Freinage Attenuateur de sons emis dans l'air
GB2276837B (en) * 1993-04-05 1997-08-06 Ford Motor Co Apparatus and method for cleaning a workpiece
WO2013001205A1 (fr) * 2011-06-29 2013-01-03 L'air Liquide,Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Buse de projection de glace seche, notamment de glace carbonique
CN115151379A (zh) * 2019-12-31 2022-10-04 冷喷有限责任公司 用于增强的喷射流的方法和装置

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2000210837A (ja) * 1999-01-25 2000-08-02 Yokogawa Kazuhiko 圧縮した気体を使った加工点冷却加工用ノズル
FR2850139B1 (fr) * 2003-01-16 2006-04-14 Herve Simoens Accessoire pour dispositif de decharge brusque d'air et dispositif de decharge equipe de cet accessoire
DE102006015805A1 (de) * 2006-04-03 2007-10-04 Alfred Kärcher Gmbh & Co. Kg Strahlmittelaustragsdüse

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2074437A5 (fr) * 1969-12-29 1971-10-01 Norton Co
US4184638A (en) * 1977-05-02 1980-01-22 Kabushiki Kaisha Toyota Chuo Kenkyusho Low noise level, pressure fluid spouting device

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2074437A5 (fr) * 1969-12-29 1971-10-01 Norton Co
US4184638A (en) * 1977-05-02 1980-01-22 Kabushiki Kaisha Toyota Chuo Kenkyusho Low noise level, pressure fluid spouting device

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2276837B (en) * 1993-04-05 1997-08-06 Ford Motor Co Apparatus and method for cleaning a workpiece
WO1996007050A1 (fr) * 1994-08-30 1996-03-07 Bosch Systemes De Freinage Attenuateur de sons emis dans l'air
WO2013001205A1 (fr) * 2011-06-29 2013-01-03 L'air Liquide,Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Buse de projection de glace seche, notamment de glace carbonique
FR2977183A1 (fr) * 2011-06-29 2013-01-04 Air Liquide Dispositif de projection de glace seche, notamment de glace carbonique
CN115151379A (zh) * 2019-12-31 2022-10-04 冷喷有限责任公司 用于增强的喷射流的方法和装置

Also Published As

Publication number Publication date
ATE109030T1 (de) 1994-08-15
EP0414863A1 (fr) 1991-03-06
EP0414863B1 (fr) 1994-07-27
JPH03504824A (ja) 1991-10-24
DE69011014T2 (de) 1995-03-23
DE69011014D1 (de) 1994-09-01

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