DE476694C - Device for stopping exhaust gas gyro fans - Google Patents

Device for stopping exhaust gas gyro fans

Info

Publication number
DE476694C
DE476694C DEA50120D DEA0050120D DE476694C DE 476694 C DE476694 C DE 476694C DE A50120 D DEA50120 D DE A50120D DE A0050120 D DEA0050120 D DE A0050120D DE 476694 C DE476694 C DE 476694C
Authority
DE
Germany
Prior art keywords
turbine
exhaust gas
fans
propellant flow
flap
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
Application number
DEA50120D
Other languages
German (de)
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.)
BBC Brown Boveri France SA
Original Assignee
BBC Brown Boveri France SA
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.)
Publication date
Priority to DEA50120D priority Critical patent/DE476694C/en
Application granted granted Critical
Publication of DE476694C publication Critical patent/DE476694C/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B33/00—Engines characterised by provision of pumps for charging or scavenging
    • F02B33/44—Passages conducting the charge from the pump to the engine inlet, e.g. reservoirs
    • F02B33/446—Passages conducting the charge from the pump to the engine inlet, e.g. reservoirs having valves for admission of atmospheric air to engine, e.g. at starting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)

Description

Einrichtung zur Stillsetzung von Abgas-Kreisel-Gebläsen Abgasturhinen, insbesondere solche zum Antrieb von Aufladegebläsen, sollen oft mit Unterbrechung laufen. Zum Stillsetzen der Turbinen siind deshalb die sonst zum Betrieb derselben notwendigen Abgasre zeitweise durch eine besondere Leitung und entsprechende UmsteUorganie unter Umgehung der Turbine abzuführen. Dadurch ergeben sich umständ-- liche und teure Bauweisen. Die vorliegende Erfindung betrifft nun eine vereinfachte Einxchtwng dieser Art. Die Er- findung besteht darin, daß ein einziges Um- schaltorgan im Innern der Turbine selbst angeoirdnet ist, welches in >der einen Grenz- lage dem Treibmittelstrem den. Weg durch die Beschauflung der Turbine versperrt .und einen solchen vom Eintrittsraum der Tur- bine nach deren Austrittsraum freigibt, wäh- rend das Umschalltorgan in der anderen Grenzlage den Treibmthelstrom zwingt, durch Düsen und Bescha;uflung -der Turbine hin- durchzustreichen. Eine besondere Umgehungs- leitung ist deshalb nicht notwendig. In der Zelchnung ist der Erfindungsgegen- stand in Verbindung mit @einenn Aufl;adege- bläse zur Darstellung gebracht. i ist die Abgasturbine und i o das Auf - la.degebläse. Die Betriebsgase werden durch die Zugasaieltung a in den Druckraum 3 ein- geführt, gelangen über das Turbinenrad 8 in den Abgasrauen q. und werden durch die Ab- gasIeitung 5 abgeführt. Zwischen Druckraum 3 und Abgasraum q ist eine bewegliche Klappe leingebaut, welche beim Betrieb diex Turbine die gezeichnete Stellung (einnimmt, d. h. Druckraum Lord Ab@ gasrauen sind voneinander getrennt. Soll nun die Turbine sitillgesetzt werden, so, wird die Klappe 7 vermittels des Hebels i- nach links in die strichpunktiert gezeich- nete Lage heruntergedreht. Dadurch wird zwischen dem Druckraum 3 und der Abgas- leitung 5 eine unmittelbare Verbindung her- gestellt und den Gasen gleichzeitig der Weg über das Turbinienrad 8 verschlossen. So wird mit einfachen Mitteln eureicht, daß die Gase wirkungslos das Turbinengehäuse durchströ- men lcdnnten; eitre besondere Umgehungslei- tung 9 (strichpwrkti:ert), wie bisher üblich, ist nicht notwandig. Treibt die ein Aufladegebläse io an, so- müßte die Verbrennungsluft auch bei stillgesetzter Turbine das Gebläse durch- strömen. Um dies zu vermeiden, muß eine Klappe i i nach dem Gebläse geöffnet werden. Diese Klappe kann nun mit dem Umsteuer- hebel der Turbine verbunden und verstellt werden. Wird dies in der angegebenen Art gemacht, so wirken die Kräfte auf die beiden Umste71organeeinander entgegen, indem der Üb,erdxuck des Gases auf die Klappe 7 links- drehend und der üb-erdruclz des Auflade- gebläses auf die Klappe i rechtsdrehend wirkt. Die für die Verstellung der Klappen notwendige Kraft ist deshalb gering. Ähn- lich wie bei; der Abgasturbine wird beim öffnen der Klappe i i in die strichpunktierte Lage der Weg der Luft durch den Verdichter abgesperrt. Device for stopping exhaust gas centrifugal fans Exhaust turbines, especially those for Drive of supercharger, should often with Run interruption. To stop the Turbines are therefore the ones normally used for operation the same necessary exhaust gas from time to time a special line and appropriate UmsteUorganie bypassing the turbine to dissipate. This results in inconveniences lich and expensive construction methods. The present invention now relates to a simplified arrangement of this kind. finding is that a single environment switching element inside the turbine itself is arranged, which is in> the one border lied to the propellant stress. Way through the blading of the turbine is blocked. and one from the entrance area of the bine releases according to their exit space, while rend the Umschalltorgan in the other Borderline forces the Treibmthelstrom through Nozzles and procurement of the turbine to cross out. A special bypass line is therefore not necessary. In the billing, the object of the invention is was in connection with @einenn Aufl; adege- blower brought to the display. i is the exhaust gas turbine and io is the la.degebläse. The operating gases are through the access point a in the pressure chamber 3 out, get through the turbine wheel 8 in the exhaust gas pipes q. and are through the ab- gas line 5 discharged. Between pressure chamber 3 and exhaust gas chamber q a movable flap is built in, which when operating the x turbine the one shown Position (occupies, i.e. pressure room Lord Ab @ gas rough are separated from each other. If the turbine is now to be shut down, so, the flap 7 is opened by means of the lever i- to the left in the dash-dotted line Nice position turned down. This will between the pressure chamber 3 and the exhaust gas line 5 establishes a direct connection and the gases at the same time the way closed via the turbine wheel 8. So will with simple means you do not know that the gases ineffective flow through the turbine housing men lcdnnten; own special bypass tion 9 (dashed letter: ert), as usual, is not necessary. Drives the a supercharger OK, so should the combustion air too when the turbine is shut down, the fan stream. To avoid this, a Flap ii can be opened after the fan. This flap can now be operated with the reversing Turbine lever connected and adjusted will. If this is done in the specified manner made, this is how the forces act on both of them Circumstances oppose each other, in that the Press the gas on the flap 7 on the left turning and the overpressure of the charging blower on the flap i clockwise works. The one for adjusting the flaps the necessary force is therefore small. Similar- lich as with; the exhaust turbine is at open the flap ii in the dash-dotted line Location of the path of air through the compressor locked.

Claims (1)

PATENTANSPRÜCHE: i. Einrichtung zur Stillsetzung von Ab- gas-Kreisel-Gebläsen ohne Unterbrechung des TreibmIttelstromes, dadurch gakenn- zeichnet, daß -ein einziges Umschaltorgan im Innern der Turbine selbst angeordnet ist, welches in. derr leinen Grenzlage dem Treibmitteiistrom den WW durch die Be- schauflung der Turbine versperrt und einen solchen vom Eöntnittsraum der Tur- bine nach deren Austrittsraum freigibt, während das Umschaltorgan in der andie- renGrenzlage den Treibmittelstrom zwingt, durch Düsen und Biescliaufung der Tur- bine hindurchzustreichen. a. Einniehtung nach Anspruch i, dadurch gekennzeichnet, daß bei Antrieb eines Auf- ladegebläs:es die Umschaltvorrichtung der AbgastuTbine mit seiner Klappe des Auf- Jadegebläses zwecks gleüchmeWger Unter- brechung der Turbinen- und Verdvcht er- beawfschlagung vdrbunden ist.
PATENT CLAIMS: i. Device for the shutdown of gas centrifugal fans without interruption of the propellant flow, thereby gakenn- draws that -a single switching device arranged inside the turbine itself is, which in the small border situation the Propellant flow through the The turbine blade is blocked and one from the opening of the tur- bine releases after their exit space, while the switching element in the andie- ren limit forces the propellant flow, through nozzles and blowing of the tur- to stroke through. a. Fitting according to claim i, characterized marked that when driving a lift loading blower: it is the switching device of the Exhaust tube with its flap of the upper Jade blower for the purpose of equilibrium breaking of the turbine and evaporator application is vdrbunden.
DEA50120D 1927-02-21 Device for stopping exhaust gas gyro fans Expired DE476694C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEA50120D DE476694C (en) 1927-02-21 Device for stopping exhaust gas gyro fans

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DEA50120D DE476694C (en) 1927-02-21 Device for stopping exhaust gas gyro fans
DE285811X 1927-02-21

Publications (1)

Publication Number Publication Date
DE476694C true DE476694C (en) 1929-05-23

Family

ID=25777153

Family Applications (1)

Application Number Title Priority Date Filing Date
DEA50120D Expired DE476694C (en) 1927-02-21 Device for stopping exhaust gas gyro fans

Country Status (1)

Country Link
DE (1) DE476694C (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE748261C (en) * 1939-06-28 1944-10-30 Method for regulating the blower pressure of an internal combustion engine charged by means of an exhaust gas turbo blower
DE906162C (en) * 1943-02-28 1954-03-11 Karl Leist Dr Ing Switching element for hot gas
DE1045037B (en) * 1952-04-30 1958-11-27 Alfred Buechi Dr Ing Turbine driven centrifugal compressor or pump
DE1183742B (en) * 1961-03-01 1964-12-17 Brown Tractors Ltd Switchable bypass device on the turbine of an exhaust gas turbocharger

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE748261C (en) * 1939-06-28 1944-10-30 Method for regulating the blower pressure of an internal combustion engine charged by means of an exhaust gas turbo blower
DE906162C (en) * 1943-02-28 1954-03-11 Karl Leist Dr Ing Switching element for hot gas
DE1045037B (en) * 1952-04-30 1958-11-27 Alfred Buechi Dr Ing Turbine driven centrifugal compressor or pump
DE1183742B (en) * 1961-03-01 1964-12-17 Brown Tractors Ltd Switchable bypass device on the turbine of an exhaust gas turbocharger

Similar Documents

Publication Publication Date Title
DE2042478C3 (en) Gas turbine engine, preferably jet engine for aircraft, with cooling air and optionally sealing air extraction
DE476694C (en) Device for stopping exhaust gas gyro fans
DE1809902C3 (en) Multi-stage turbo molecular high vacuum pump
GB968069A (en) Gas turbine jet propulsion engine
DE897634C (en) Exhaust gas turbine system for internal combustion engines with partial admission of the turbine blades
DE953280C (en) Multi-stage blasting device for venting pumps, containers, etc. like
DE362887C (en) Method and device for increasing the pressure in centrifugal blowers
AT208920B (en) Device for venting the engine compartment on vehicles with internal combustion engine drives
DE563008C (en) Method for distributing the means conveyed by at least one conveyor device to different consumers and devices for carrying out this method
DE892401C (en) Application regulation for turbines, especially fresh gas and exhaust gas turbines
DE710787C (en) Two-stage or multi-stage steam jet air extractor with switch-off, parallel switched start-up stage, especially for condensation systems
DE1023638B (en) Device for braking a unit driven by a gas turbine system, in particular a motor vehicle
CH246174A (en) Recoil engine for means of transport, in particular aircraft.
AT45549B (en) Device for introducing additional air into the combustion chamber.
DE670456C (en) Control device for the braking process
DE354587C (en) Adjustable ejector suction for combustion systems
DE353784C (en) Pull arrangement for suction and pressure pull by means of two fans
DE729879C (en) Device for influencing the boundary layer on aircraft wings
DE665584C (en) Device for the blow-out operation in internal combustion engines operated with a centrifugal blower
DE2057557B2 (en) PIPE MAIL SYSTEM WITH RESERVE BLOWER
DE1245750B (en) Twin-flow gas turbine jet engine with gas and air deflectors
DE967839C (en) Control device for a multi-stage axial compressor with variable speed
DE753770C (en) Device for regulating the temperature of the heated cabin of an altitude aircraft
DE875177C (en) Pneumatic tube system with closed air circuit
DE230120C (en)