DE869446C - Metal combustion chamber for the generation of hot gases, especially propellants for gas turbine systems - Google Patents
Metal combustion chamber for the generation of hot gases, especially propellants for gas turbine systemsInfo
- Publication number
- DE869446C DE869446C DEA12884A DEA0012884A DE869446C DE 869446 C DE869446 C DE 869446C DE A12884 A DEA12884 A DE A12884A DE A0012884 A DEA0012884 A DE A0012884A DE 869446 C DE869446 C DE 869446C
- Authority
- DE
- Germany
- Prior art keywords
- perforated
- combustion chamber
- jacket
- sections
- hole cross
- 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
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/20—Heat transfer, e.g. cooling
- F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Description
Heiße Verbrennungsgase für mancherlei Verwendungszwecke, insbesondere Treibgase für Gasturbinenanlagen, werden in bekannter Weise in metallenen Brennkammern mit Doppelmantel erzeugt; dabei wird' die Brenn- und Kühlluft teilweise dem vom Innenmantel umschlossenen Brennraum durch Öffnungen im Innenmantel aus dem zwischen den beiden Mänteln liegenden Raum zugeführt. Es ist aber auch bekannt, zwecks Verhinderung der Bildung einer Grenzschicht heißer Gase, sowohl an der Innen- wie auch an der Außenwand des Innenmantels und zwecks Wegblasens des· an der heißen Innenwand entstehenden Brennstoffdampfes, einen Teil der Brenn- und Kühlluft durch den über den hitzegefährdetsten Teil seiner Oberfläche siebartig ausgebildeten Innenmantel in radialer Richtung nach innen in den Brennraum einzuführen. Durch die radial in den Brennraum einströmende Luft werden die Grenzschichten beidseitig des Innenmantels ständig erneuert und so dessen Kühlung verbessert.Hot combustion gases for various purposes, in particular propellants for gas turbine systems are known in generated metal combustion chambers with double jacket; thereby 'the combustion and cooling air is partially the combustion chamber enclosed by the inner jacket through openings in the inner jacket from the between supplied to the two coats lying space. But it is also known for the purpose of preventing the Formation of a boundary layer of hot gases, both on the inner as well as on the outer wall of the inner jacket and for the purpose of blowing away the fuel vapor generated on the hot inner wall, a Part of the combustion and cooling air through the screen-like over the most heat-endangered part of its surface trained inner jacket in the radial direction to introduce inward into the combustion chamber. By the air flowing radially into the combustion chamber becomes the boundary layers on both sides of the inner jacket constantly renewed and so its cooling improved.
Indessen hat es sich gezeigt, daß eine so gebaute Brennkammer einige Nachteile aufweist. Insbesondere wird der durch die Flamme unmittelbar erhitzte Innenmantel dadurch stark belastet, daß er den ganzen Druckabfall aufnehmen muß. Auch wird die Luft durch die Löcher mit großer Geschwindigkeit in den Brennraum eingeblasen, wasIn the meantime it has been shown that a Combustion chamber has some disadvantages. In particular, the one directly heated by the flame Inner jacket is heavily loaded because it has to absorb the entire pressure drop. Even the air is blown through the holes at high speed into the combustion chamber, what
eine starke Abkühlung der Flamme mit sich bringt. Schließlich wird auch dieser Druckabfall zu wenig wirksam zur Kühlung des Innenmantels ausgenutzt. Die erwähnten Nachteile werden behoben, wenn der Innenmantel seinerseits wiederum' doppelwandig ausgeführt wird. Die Erfindung betrifft so-' mit "eine metallene Brennkammer mit Außen- und Innenmatitel zur Erzeugung heißer Gase, insbesondere Tre'ibgase für Gasturbinenanlagen, bei welcherbrings about a strong cooling of the flame. Ultimately, this pressure drop is also too little effectively used to cool the inner jacket. The disadvantages mentioned are eliminated when the inner jacket in turn is double-walled. The invention relates to so- ' with "a metal combustion chamber with external and Inside titles for the generation of hot gases, in particular Tre'ib gases for gas turbine plants, in which
ίο die Brenn- und Kühlluft teilweise dem vom Innenmantel umschlossenen Brennraum durch öffnungen im Innenmantel aus dem zwischen den beiden Mänteln liegendem Raum zugeführt wird, und besteht darin, daß der hitzegefährdetste . Teil des Innenmantels seinerseits wiederum aus mindestens zwei k'onzentrisch angeordneten Lochmänteln besteht, die beidseitig luftdicht aneinander- angeschlossen sind, so daß zwischen den einzelnen Lochmänteln geschlossene Ringräume vorhanden sind.ίο the combustion and cooling air partly that of the inner jacket enclosed combustion chamber through openings in the inner jacket from between the two Coats is fed lying space, and is that the most heat endangered. part of The inner jacket in turn consists of at least two concentrically arranged perforated jackets, which are connected to one another airtight on both sides, so that between the individual perforated shells closed annulus spaces are available.
In der Zeichnung ist in einem Vertikalschnitt^ durch die Achse ein Ausführungsbeispiel mit zwei konzentrischen Lochmänteln einer Brennkammer gemäß der Erfindung dargestellt.In the drawing is in a vertical section ^ through the axis an embodiment with two concentric perforated casings of a combustion chamber shown according to the invention.
Mit ι ist die Zuleitung der verdichteten B renn -With ι the feed line of the compressed B renn -
und Kühlluft bezeichnet, 2 ist der Außenmantel und 3 den Innenmantelder Brennkammer. Letzterer besteht' im gezeigten Beispiel aus einem innerenand denotes cooling air, 2 is the outer jacket and 3 is the inner jacket of the combustion chamber. The latter consists of an inner one in the example shown
Lochmantel 36 und einem äußeren Lochmantel 3a . sowie einem Mantelteil 3^ welcher keine siebartige Durchlochung aufweist, weil er nicht zum hitzegefährdetsten, in unmittelbarer Nähe der FlammePerforated jacket 3 6 and an outer perforated jacket 3 a . as well as a jacket part 3 ^ which has no sieve-like perforation, because it is not the most heat-endangered, in the immediate vicinity of the flame
■: gelegenen Teil, des Innenmantels gehört. Der Auslaß für die heißen Venbrennungsgase ist bei 4 gezeigt. Bei 5 ist ein um die Brennstoffzuführung 6 herum angeordneter Drallkörper angedeutet, 7 ist der Raum zwischen dem Innen- und dem Außenmantel, und mit 8 ist der Ringraum zwischen den beiden gezeigten Lochmänteln 3° und 3& bezeichnet. Dies ist, abgesehen von den Luftlöchern in den Lochmänteln selbst, ein geschlossener: Ringraum,■: part that belongs to the inner jacket. The outlet for the hot combustion gases is shown at 4. At 5 a swirl body arranged around the fuel supply 6 is indicated, 7 is the space between the inner and outer casing, and 8 is the annular space between the two perforated casings shown 3 ° and 3 & quot ;. Apart from the air holes in the perforated sheaths themselves, this is a closed one: annulus,
d. h. er ist an beiden Enden, in der Zeichnung an dem an den Drallkörper 5 anschließenden oberen,d. H. it is at both ends, in the drawing on the upper adjoining swirl body 5,
. kegelförmigen Ende sowie an dem innerhalb des. conical end as well as at the inside of the
Mantelteils 3? - liegenden 'unteren, ringförmigen Ende, luftdicht abgeschlossen. Mit 9 sind die Löcher in den Lochmänteln bezeichnet. Die Summe . der Lochquerschnitte des innersten Lochmantels ■kann gleich groß sein wie die Summe der Lochquerschnitte der äußeren Lochmäntel oder aber sie kann größer sein, derart, daß der innerste Lochmantel nur durch einen Bruchteil des gesamten Druckabfalles der durch den Innenmantel strömenden Luft belastet ist. Sind mehr als zwei konzentrische Lochmäntel vorgesehen, so ist es zweckmäßig, die Lochquerschnitte der einzelnen Lochmäntel so zu verteilen, daß der den innersten Lochmantel umgebende Lochmantel die kleinste Summe der Lochquerschnitte hat. Bei 10 sind größere Lufteintrittsöffmingen gezeigt; die sich im nicht siebartig gelochten Teil des inneren Brennkammer^ mantels befinden können. Zwischen einzelnen Teilen des Innenmantels, wie beispielsweise bei 11, oder an dessen Ende, z,. B. bei 12, können sich auch ringförmige Lufteintrittsschlitze befinden.Shell part 3? - lying 'lower, annular End, hermetically sealed. With 9 the holes in the perforated sheaths are designated. The sum . the hole cross-sections of the innermost perforated jacket ■ can be the same size as the sum of the hole cross-sections the outer perforated jacket or it can be larger, so that the innermost perforated jacket only through a fraction of the total Pressure drop of the air flowing through the inner jacket is loaded. Are more than two concentric Perforated jackets are provided, so it is useful to determine the hole cross-sections of the individual perforated jackets to be distributed in such a way that the perforated jacket surrounding the innermost perforated jacket has the smallest sum which has hole cross-sections. At 10 there are larger air inlet openings shown; which is in the not perforated part of the inner combustion chamber ^ mantle can be located. Between individual parts of the inner jacket, such as at 11, or at the end of it, z. B. at 12, there can also be annular air inlet slots.
Die beschriebene Bauweise einer metallenen Brennkammer bietet folgende Vorteile: Der durch die Hitze der Flamme am meisten gefährdete Teil des Innenmantels wird mechanisch entlastet und dadurch das Gewicht dieses dem Verschleiß unterworfenen Elementes verringert. Die Luft tritt mit kleinerer Geschwindigkeit in den Brennraum ein und verhindert so eine intensive Kühlung der Flamme. Der innere Lochmantel wird durch viele kleine Luftstrahlen von außen gekühlt.The described construction of a metal combustion chamber offers the following advantages: The through the heat of the flame most endangered part of the inner jacket is mechanically relieved and thereby reducing the weight of this element subject to wear. The air comes with it enters the combustion chamber at a lower speed, thus preventing intensive cooling of the Flame. The inner perforated jacket is cooled from the outside by many small jets of air.
Claims (4)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH706645X | 1950-09-04 |
Publications (1)
Publication Number | Publication Date |
---|---|
DE869446C true DE869446C (en) | 1953-03-05 |
Family
ID=4530435
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DEA12884A Expired DE869446C (en) | 1950-09-04 | 1951-02-11 | Metal combustion chamber for the generation of hot gases, especially propellants for gas turbine systems |
Country Status (5)
Country | Link |
---|---|
US (1) | US2654219A (en) |
CH (1) | CH284190A (en) |
DE (1) | DE869446C (en) |
FR (1) | FR1041182A (en) |
GB (1) | GB706645A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3767122A (en) * | 1971-08-10 | 1973-10-23 | Lucas Aerospace Ltd | Flame tubes |
DE2355547A1 (en) * | 1972-11-10 | 1974-05-16 | Gen Electric | DOUBLE WALL BURNER WITH IMPACT COOLING |
Families Citing this family (38)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL84788C (en) * | 1951-06-12 | |||
US2775293A (en) * | 1952-09-16 | 1956-12-25 | Hupp Corp | Liquid fuel fired heating apparatus for use, especially on automotive conveyances |
BE535497A (en) * | 1954-02-26 | |||
NL248467A (en) * | 1957-02-18 | |||
US3057611A (en) * | 1960-02-15 | 1962-10-09 | Bjerkan Engineering Service In | Burner-blower combination for grain dryers |
US3251356A (en) * | 1963-02-20 | 1966-05-17 | Hupp Corp | Radiant heating device |
US3220460A (en) * | 1963-04-12 | 1965-11-30 | Colt Ventilation & Heating Ltd | Heat generators |
US3185458A (en) * | 1963-05-13 | 1965-05-25 | Zink Co John | Direct fired air heater |
US3443799A (en) * | 1966-12-19 | 1969-05-13 | Alco Standard Corp | Air heating systems |
US3463467A (en) * | 1967-05-29 | 1969-08-26 | Midland Ross Corp | All-metal high capacity burner |
US3576384A (en) * | 1968-11-29 | 1971-04-27 | British American Oil Co | Multinozzle system for vortex burners |
US3729287A (en) * | 1971-08-23 | 1973-04-24 | Amoco Prod Co | Flare windshield |
DE2224711A1 (en) * | 1972-05-20 | 1973-11-29 | Eberspaecher J | HEATING DEVICE PREFERRED FOR VEHICLES WITH WATER-COOLED COMBUSTION ENGINE |
US4174608A (en) * | 1972-08-15 | 1979-11-20 | Stal-Laval Turbin Ab | Combustion chamber for a gas turbine |
US3922851A (en) * | 1974-04-05 | 1975-12-02 | Gen Motors Corp | Combustor liner support |
GB1498034A (en) * | 1974-05-14 | 1978-01-18 | Secr Defence | Dinghies |
US3975141A (en) * | 1974-06-25 | 1976-08-17 | The United States Of America As Represented By The Secretary Of The Army | Combustion liner swirler |
US4141213A (en) * | 1977-06-23 | 1979-02-27 | General Motors Corporation | Pilot flame tube |
GB2049152B (en) * | 1979-05-01 | 1983-05-18 | Rolls Royce | Perforate laminated material |
US4276018A (en) * | 1979-05-30 | 1981-06-30 | Davey Compressor Co. | Mobile heater |
DE3663847D1 (en) * | 1985-06-07 | 1989-07-13 | Ruston Gas Turbines Ltd | Combustor for gas turbine engine |
US4626201A (en) * | 1985-06-11 | 1986-12-02 | Grantham Charles R | Combustion chamber for a commercial laundry dryer |
US5096412A (en) * | 1991-01-28 | 1992-03-17 | The United States Of America As Represented By The Secretary Of The Army | Combustion chamber for multi-fuel fired ovens and griddles |
EP0990851B1 (en) * | 1998-09-30 | 2003-07-23 | ALSTOM (Switzerland) Ltd | Gas turbine combustor |
US6394795B2 (en) | 1999-03-11 | 2002-05-28 | Eclipse, Inc. | Air heating burner |
US6349467B1 (en) * | 1999-09-01 | 2002-02-26 | General Electric Company | Process for manufacturing deflector plate for gas turbin engine combustors |
US6351947B1 (en) | 2000-04-04 | 2002-03-05 | Abb Alstom Power (Schweiz) | Combustion chamber for a gas turbine |
JP3962554B2 (en) * | 2001-04-19 | 2007-08-22 | 三菱重工業株式会社 | Gas turbine combustor and gas turbine |
US6964170B2 (en) * | 2003-04-28 | 2005-11-15 | Pratt & Whitney Canada Corp. | Noise reducing combustor |
US6971242B2 (en) * | 2004-03-02 | 2005-12-06 | Caterpillar Inc. | Burner for a gas turbine engine |
US7762074B2 (en) * | 2006-04-04 | 2010-07-27 | Siemens Energy, Inc. | Air flow conditioner for a combustor can of a gas turbine engine |
US7856830B2 (en) * | 2006-05-26 | 2010-12-28 | Pratt & Whitney Canada Corp. | Noise reducing combustor |
US7628020B2 (en) * | 2006-05-26 | 2009-12-08 | Pratt & Whitney Canada Cororation | Combustor with improved swirl |
US7788926B2 (en) * | 2006-08-18 | 2010-09-07 | Siemens Energy, Inc. | Resonator device at junction of combustor and combustion chamber |
US8622737B2 (en) * | 2008-07-16 | 2014-01-07 | Robert S. Babington | Perforated flame tube for a liquid fuel burner |
US8104288B2 (en) * | 2008-09-25 | 2012-01-31 | Honeywell International Inc. | Effusion cooling techniques for combustors in engine assemblies |
EP2405200A1 (en) * | 2010-07-05 | 2012-01-11 | Siemens Aktiengesellschaft | A combustion apparatus and gas turbine engine |
DE102016207057A1 (en) * | 2016-04-26 | 2017-10-26 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustor |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US812513A (en) * | 1905-02-27 | 1906-02-13 | Luigi Moreno | Apparatus for burning gas. |
US2164954A (en) * | 1936-10-06 | 1939-07-04 | Thomas J Stephens | Combustion and gas mixing assembly for gas circulating systems |
US2498728A (en) * | 1948-05-07 | 1950-02-28 | Westinghouse Electric Corp | Combustion apparatus |
-
1950
- 1950-09-04 CH CH284190D patent/CH284190A/en unknown
-
1951
- 1951-02-11 DE DEA12884A patent/DE869446C/en not_active Expired
- 1951-08-17 FR FR1041182D patent/FR1041182A/en not_active Expired
- 1951-08-28 US US244047A patent/US2654219A/en not_active Expired - Lifetime
- 1951-09-04 GB GB20864/51A patent/GB706645A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3767122A (en) * | 1971-08-10 | 1973-10-23 | Lucas Aerospace Ltd | Flame tubes |
DE2355547A1 (en) * | 1972-11-10 | 1974-05-16 | Gen Electric | DOUBLE WALL BURNER WITH IMPACT COOLING |
Also Published As
Publication number | Publication date |
---|---|
FR1041182A (en) | 1953-10-21 |
GB706645A (en) | 1954-03-31 |
CH284190A (en) | 1952-07-15 |
US2654219A (en) | 1953-10-06 |
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