US3667241A - Construction of a chamber for cooling hot gases - Google Patents

Construction of a chamber for cooling hot gases Download PDF

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Publication number
US3667241A
US3667241A US16006A US3667241DA US3667241A US 3667241 A US3667241 A US 3667241A US 16006 A US16006 A US 16006A US 3667241D A US3667241D A US 3667241DA US 3667241 A US3667241 A US 3667241A
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US
United States
Prior art keywords
gases
coolant
chamber
outlet
flow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US16006A
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English (en)
Inventor
German Munding
Willi Zeh
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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
Priority claimed from DE19691911078 external-priority patent/DE1911078C/de
Priority claimed from DE19691930990 external-priority patent/DE1930990C3/de
Application filed by Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Application granted granted Critical
Publication of US3667241A publication Critical patent/US3667241A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28C—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA COME INTO DIRECT CONTACT WITHOUT CHEMICAL INTERACTION
    • F28C3/00—Other direct-contact heat-exchange apparatus

Definitions

  • a construction of a chamber for cooling hot gases such as fuel gases or combustion gases includes means for introducing the hot gases into the chamber in a whirling flow and into contact with a coolant which is preferably in solid form and is located within the chamber. The gases contact the coolant and cause the coolant to slowly dissolve while the gases are cooled down.
  • the coolant is advantageously made of a L-shaped cross-sectional configuration and it includes a wall which surrounds the outlet to the chamber, and which forms, with the chamber wall, an over flow weir for the outflow of the gases after they have been cooled within the chamber.
  • the coolant itself advantageously includes means such as longitudinally extending grooves for forming rotatable eddies on the whirling gas flow which intensify the heat exchange between the relatively cooled boundary layer and the hotter rotating layers of the whirling gas flow located further inside radially.
  • the coolant chamber advantageously includes a front wall or closed wall located opposite the outlet which car ries the coolant lining in a solid form.
  • This invention relates in general to a cooling chamber construction and in particular, to a new and useful cooling chamber construction for treating hot gases particularly combustion gases or fuel gases and particularly for cooling such gases with a coolant preferably in a solid form.
  • Gases which are produced in combustion chambers with the combustion of fuel with oxygen and particularly gases produced in rocket combustion chambers which employ an oxygen carrier and a fuel usually have a very high temperature so that they are unsuited, without cooling, for various fields of applications such as for driving gas turbines or for use as pressure gases for the transport of fuel components for rocket engines.
  • combustion chambers such as those which use an airoxygen combustion, as much air is admixed to the hot flame core, which is produced in the front part of the fire box, as is needed to attain the drop in temperature required for a succeeding heat sensitive machine. such as a turbine which will be highly stressed from a strength standpoint.
  • Fuel gases produced, often in a vacuum, by rocket firing processes cannot be supplied with air to reduce their temperature for technological reasons.
  • cooling chamber after the combustion chamber for lowering the temperature of the gases.
  • a cooling chamber is usually filled with a solid chemical coolant of endothermic characteristics such as ammonium oxalade having a plurality of longitudinal holes extending therethrough.
  • the very hot fuel gases flow through the holes and thereby dissolve the coolant while the gases themselves become cooled.
  • the coolant then mixes in a gaseous form with the fuel gas, for example as described in the issue of Space Aeronautics of October 1961 on pages 75 and 76. Since it takes a certain time, and hence a certain length of coolant, to dissolve the coolant itself and also to cool the fuel gases, the cooling chamber must have an appropriate length. In rockets and space craft in which the structural dimensions play an essential role the structural length required for the known cooling chamber is not always available or is extremely difficult to provide.
  • the cooling chamber is lined with a solid coolant of substantially L-shaped cross sectional configuration and one leg of the coolant is located to extend radially inwardly into the coolant chamber adjacent the outlet thereof.
  • the coolant forms an overflow weir which ensures a sufficiently long dwell of the fuel gases within the spin chamber to provide a satisfactory cooling action. This also enhances the erosion action on the coolant and also provides for a greater heat exchange between the various revolving layers of the helically progressive flow of hot gases within the cooling chamber.
  • a plurality of grooves preferably those which extend in a longitudinal direction and are parallel to each other are provided around the interior wall of the coolant and they produce rotatable eddies which intensify the heat exchange between the boundary layer of the gases which already contact the coolant and with the outer higher temperature gases which are continuously being tangentially directed into the cooling chamber.
  • the cooling chamber is lined with a solid coolant at the interior or closed end adjacent the wall which is opposite to the outlet and the secondary return currents in the form of a toroid which are generated are utilized for the ablation of the solid coolant.
  • the gases which reach the coolant lining at the front face wall of the chamber along with the secondary return currents in the form of a toroid which are generated in the central area of the chamber move radially outwardly past the coolant lining and dissolve much of the coolant as they move.
  • the gases thus are cooled down very rapidly and as they reach the radially external chamber area, they are thoroughly mixed with the rotating gas layers of the primary whirling gas flow which intersect their flow path in that area so that they too experience a lowering of their temperature.
  • the cooled rotating gas layers then move radially outwardly, because of their greater specific gravity, under the influence of centrifugal force and they displace the still uncooled relatively hot gases in a radially inward direction where these hot gases become included in the secondary return flows in the form of a toroid and are brought by them into contact with the coolant lining of the front face wall of the chamber.
  • Tests have proven that the implementation form of the cooling chamber according to the invention and operating in this manner furnishes excellent cooling results.
  • a further object of the invention is to provide a cooling chamber construction which includes an interior having a solid coolant lining advantageously formed with a plurality of longitudinally extending grooves for the production of rotatable eddies and also preferably including a radially inwardly extending leg portion adjacent the outlet of the cooling chamber forming a weir for controlling the outflow of the gases as they are cooled and wherein the chamber includes means for tangentially directing the high temperature gases to be cooled into the chamber in a whirling flow proceeding from the closed end and progressing in a helical spiral around the interior walls toward the outlet.
  • a further object of the invention is to provide a cooling chamber which includes means for tangentially introducing high temperature gases into the chamber adjacent a closed end in a whirling axially progressing flow for movement toward an outlet end and which advantageously includes a solid coolant arranged at the closed end and preferably covering an area corresponding to a centrally arranged outlet at the opposite end.
  • a further object of the invention is to provide a cooling chamber for high temperature gases to facilitate their use in devices which require gases at a lower temperature and which is simple in design, rugged in construction, and economical to manufacture.
  • a further object of the invention is to provide a method of treating high temperature gases in order to cool them which comprises tangentially directing them into a cooling chamber to flow in a whirling stream which proceeds in an axial direction and brings about secondary axially oriented return flows in the form of toroid, and moving them into contact with a solid coolant as they are so flowing while generating rotatable eddies on the whirling gas stream to facilitate erosion of the coolant and an intermixing of the gases, and permitting the cooled gases to flow outwardly through a centrally located outlet which is bounded by a wall which functions as a weir to permit an overflow of the cooled gases through the outlet.
  • a further object of the invention is to provide a method of treating high temperature gases in order to cool them which comprises tangentially directing them into a cooling chamber to flow in a whirling stream which proceeds in an axial direction and brings about secondary axially oriented return flows in the form of a toroid, and moving said secondary axially oriented return flows into contact with a solid coolant, and permitting the cooled gases to flow outwardly through a centrally located outlet which is bounded by a wall which functions as a weir to permit an overflow of the gases through the outlet.
  • FIG. 1 is a longitudinal sectional view of a cooling chamber constructed in accordance with the invention
  • FIG. 2 is a section taken on the line II-II of FIG. 1;
  • FIG. 3 is a section taken on the line IIIIII of FIG. 1;
  • FIG. 4 is a view similar to FIG. 1 of another embodiment of the invention.
  • FIG. 1 a cooling device or cooling chamber vessel generally designated 10 which is made of a compressed longitudinal form with a closed end 10a and having a central opening 10b at a discharge or opposite end 100.
  • the device 10 defines a spin chamber 1 which is provided with a coolant lining 2 of generally L-shaped cross section and of a material such as a solid coolant.
  • the lining 2 includes a leg portion or annular flange 2a which lies adjacent the opened end 100 and forms an overflow weir which forms a retarded action on the longitudinal progression of the hot gas flow until the gas is sufficiently cooled to move inwardly and flow outwardly through the central opening 10b.
  • hot gases are tangentially introduced through an inlet 5 and they move in the direction of the arrow 4 in a whirling axially progressing flow around the interior wall of the device 10.
  • the interior wall of the coolant is advantageously provided with a plurality of longitudinally extending grooves 3 which cause the hot gases 4 to form rotatable eddies, 6 which intensify the heat exchange between the relatively cooled boundary layer and the hotter rotating layers located further inside radially.
  • a cooling device 10 having an inner or front closed wall 100' and an opposite wall 100 having a central opening forming an outlet 10b.
  • the device 10' includes a cylindrical wall 7 and a conical front wall 8.
  • the hot gases are tangentially admitted through openings 5 for flow in a direction of the arrow 4' and in tangential whirling directions which progress axially toward the outlet 10b.
  • the wall 8 is provided with a block of solid coolant 12 in an area which corresponds to the projection of the opening 10b but located at the front or closed end.
  • the solid coolant is of a material such as ammonium oxalade.
  • a cooling chamber construction comprising wall means defining an axially short whirl chamber of relatively great diameter, means for introducing high temperature gases tangentially into said chamber for flow adjacent the interior walls thereof, means defining an outlet at a spaced location from the means for introducing the high temperature gases, and a solid coolant block located within said chamber adjacent the walls thereof in a position to be contacted by the hot gases as they move around the walls and axially toward the outlet.
  • a cooling chamber construction according to claim 1, wherein said coolant block includes a plurality of longitudinally extending grooves therein providing means for forming a plurality of eddies of gases adjacent the wall of said coolant.
  • a cooling chamber construction according to claim 1, wherein said solid coolant is located adjacent the closed end of said chamber and opposite to the outlet.
  • a cooling chamber construction according to claim 1, wherein said solid coolant block is arranged in the closed end of said chamber opposite to said outlet and being of a size substantially equal to the size of said outlet.
  • a cooling device comprising a tubular member having a closed end and an opposite end with an opening forming a discharge, means for introducing high temperature gases at at least one location adjacent the closed end for whirling tangential flow around the interior of said tubular member and for axial movement in a helical flow toward said outlet, and a solid coolant block located within said tubular member adjacent the walls thereof in a position to be contacted by said gases.
  • a cooling device according to claim 6, wherein said solid coolant is of L-shaped cross section and includes a leg portion forming a radially inwardly extending annular flange adjacent said outlet and providing a weir for regulating the flow of the gases.
  • said coolant includes a plurality of longitudinally extending grooves therein providing means for forming a plurality of eddies of gases adjacent the wall of said coolant.
  • a cooling device according to claim 6, wherein said solid coolant is located adjacent the closed end of said tubular member and opposite to the outlet.
  • a cooling device according to claim 6, wherein said solid coolant is arranged in the closed end of said tubular member opposite to said outlet and being of a size substantially equal to the size of said outlet.
  • a method of treating high temperature gases in order to permit them to be used for devices requiring gases at a lower temperature comprising tangentially directing the gases into a whirling chamber and over the surface of a solid coolant so as to cause the gases to move against the coolant and to dissolve the coolant and to be cooled thereby.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)
US16006A 1969-03-05 1970-03-03 Construction of a chamber for cooling hot gases Expired - Lifetime US3667241A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19691911078 DE1911078C (de) 1969-03-05 Als Drallkammer ausgebildete Kammer zum Kuhlen von heißen Gasen, insbesondere Brenngasen
DE19691930990 DE1930990C3 (de) 1969-06-19 1969-06-19 Als Drallkammer ausgebildete Kammer zum Kühlen von heißen Gasen, insbesondere Brenngasen

Publications (1)

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US3667241A true US3667241A (en) 1972-06-06

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US16006A Expired - Lifetime US3667241A (en) 1969-03-05 1970-03-03 Construction of a chamber for cooling hot gases

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US (1) US3667241A (enrdf_load_html_response)
CH (1) CH496222A (enrdf_load_html_response)
FR (1) FR2034662A7 (enrdf_load_html_response)
GB (1) GB1300962A (enrdf_load_html_response)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080271465A1 (en) * 2006-10-18 2008-11-06 Cessna Aircraft Company System and method for controlling an environment in an aircraft using a vortex cooler
US9737933B2 (en) 2012-09-28 2017-08-22 General Electric Company Process of fabricating a shield and process of preparing a component

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955432A (en) * 1958-05-30 1960-10-11 Shell Oil Co Vortex tube with internal cooling
US3160490A (en) * 1959-08-14 1964-12-08 Commissariat Energie Atomique Apparatus for the continuous purification of uranium hexafluoride
US3224215A (en) * 1962-12-24 1965-12-21 Titan Gmbh Process and device for cooling a hot gas mixture containing tio2
US3534555A (en) * 1968-03-06 1970-10-20 Webb James E Laminar flow enhancement

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955432A (en) * 1958-05-30 1960-10-11 Shell Oil Co Vortex tube with internal cooling
US3160490A (en) * 1959-08-14 1964-12-08 Commissariat Energie Atomique Apparatus for the continuous purification of uranium hexafluoride
US3224215A (en) * 1962-12-24 1965-12-21 Titan Gmbh Process and device for cooling a hot gas mixture containing tio2
US3534555A (en) * 1968-03-06 1970-10-20 Webb James E Laminar flow enhancement

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080271465A1 (en) * 2006-10-18 2008-11-06 Cessna Aircraft Company System and method for controlling an environment in an aircraft using a vortex cooler
US8099966B2 (en) * 2006-10-18 2012-01-24 Textron Innovations Inc. System and method for controlling an environment in an aircraft using a vortex cooler
US9737933B2 (en) 2012-09-28 2017-08-22 General Electric Company Process of fabricating a shield and process of preparing a component
US10828701B2 (en) 2012-09-28 2020-11-10 General Electric Company Near-net shape shield and fabrication processes

Also Published As

Publication number Publication date
CH496222A (de) 1970-09-15
GB1300962A (en) 1972-12-29
FR2034662A7 (enrdf_load_html_response) 1970-12-11

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