DE3838077C1 - Device for monitoring the temperature of rocket burners during operation - Google Patents

Device for monitoring the temperature of rocket burners during operation

Info

Publication number
DE3838077C1
DE3838077C1 DE3838077A DE3838077A DE3838077C1 DE 3838077 C1 DE3838077 C1 DE 3838077C1 DE 3838077 A DE3838077 A DE 3838077A DE 3838077 A DE3838077 A DE 3838077A DE 3838077 C1 DE3838077 C1 DE 3838077C1
Authority
DE
Germany
Prior art keywords
temperature
during operation
combustion chamber
monitoring
rocket
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
DE3838077A
Other languages
German (de)
Inventor
Christoph Dipl.-Ing. 8000 Muenchen De Caesar
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
Application filed by Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Priority to DE3838077A priority Critical patent/DE3838077C1/en
Application granted granted Critical
Publication of DE3838077C1 publication Critical patent/DE3838077C1/en
Expired legal-status Critical Current

Links

Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01KMEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K7/00Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
    • G01K7/02Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
    • G01K7/08Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples the object to be measured forming one of the thermoelectric materials, e.g. pointed type
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/96Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
    • HELECTRICITY
    • H10SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10NELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10N10/00Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Measuring Temperature Or Quantity Of Heat (AREA)

Abstract

A device for monitoring the temperature of rocket burners during operation, characterised in that the burner and/or the combustion chamber consists (at least in a wall region which is subjected to high temperatures during operation) of a material which forms one pole or limb of a thermocouple, and in that one conductor is mounted on this wall region for each temperature measurement point, which conductor emits a thermocouple voltage for evaluation when interconnected with the material of the burner/the combustion chamber.

Description

Die Erfindung betrifft eine Vorrichtung zur Kontrolle von Raketenbren­ nern, insbesondere Brennkammern während des Betriebs. Gefordert wird für die bemannte Raumfahrt eine lückenlose Überwachung des Raketentriebwerks vom Start weg bis zum Ausbrennen. Im Betrieb werden Temperaturen er­ reicht in wenigstens heißen Zonen oder Bereichen der Brennkammern, die das verwendete Material bis auf Weißglut erhitzen. Für eine lückenlose Überwachung der heißen Teile eines Triebwerkes werden bisher einzelne voneinander unabhängige Temperaturmeßstellen verlegt, die einen enormen Verkabelungs-, Übertragungs- und Auswerteaufwand erfordern. Außerdem sind die Fehlermöglichkeiten vervielfacht. Im Falle eines Ablösens einer Temperaturmeßstelle vom Triebwerk werden falsche und meist zu niedrige Daten geliefert.The invention relates to a device for controlling rocket burns nern, especially combustion chambers during operation. Is required for the manned space flight a complete surveillance of the rocket engine from the start to the burnout. Temperatures become high during operation sufficient in at least hot zones or areas of the combustion chambers heat the material used to white heat. For a complete Monitoring of the hot parts of an engine has so far been individual relocated independent temperature measuring points, which is enormous Cabling, transmission and evaluation require effort. Furthermore the potential for errors are multiplied. In the event of a replacement Temperature measuring point of the engine are wrong and mostly too low Data delivered.

Optische Temperaturmeßverfahren sind wegen der erforderlichen Wärmeiso­ lierung des Triebwerks nicht anwendbar.Optical temperature measurement methods are because of the required heat Engine layout not applicable.

Aufgabe der Erfindung ist es, die Kontrolle bzw. Überwachung von Rake­ tentriebwerken vom Start weg für die gesamte Betriebsdauer mit geringem Aufwand und so fehlerfrei wie möglich durchzuführen.The object of the invention is to control or monitor rake engines from the start for the entire operating life with little Effort and as error-free as possible.

Gelöst wird diese Aufgabe durch die Merkmale des Patentanspruchs 1. In weiteren Ansprüchen sind Merkmale aufgeführt, die der Aus- und Weiter­ bildung der Erfindung dienlich sind.This problem is solved by the features of claim 1. In further claims are listed features that the expansion and further education of the invention are useful.

Die wesentlichsten Vorteile der Erfindung sind:
Daß auch ein gefährlicher Temperaturanstieg während des Starts oder Be­ Be­ triebs festgestellt werden kann und Schäden an dem Triebwerk und der Rakete, insbesondere ein Durchbrennen, rechtzeitig verhindert werden können.
The main advantages of the invention are:
That a dangerous rise in temperature during take-off or operation can be determined and damage to the engine and the missile, in particular a burnout, can be prevented in good time.

Der Raketenbrenner bzw. die Brennkammer besteht ganz oder teilweise aus einem hochtemperaturfesten (etwa 2000° C) Thermoelementmaterial. Ein Vor­ teil der Erfindung liegt darin, daß im Fall des Ablösens eines Thermo­ elementschenkels von der Brennkammerwand, dessen Signal ganz ausfällt, die restlichen Thermoelemente immer noch den gesuchten Wert für die maximale Triebwerkstemperatur mit ausreichender Zuverlässigkeit liefern. Ein Temperaturanstieg, der dem Ausfall nur einer Meßstelle bei einer kritischen Temperatur voranging, läßt auch nur auf ein einfaches Versa­ gen dieser Meßstelle schließen.The rocket burner or the combustion chamber consists entirely or partially of a high temperature resistant (about 2000 ° C) thermocouple material. A before part of the invention is that in the case of peeling a thermal element leg from the combustion chamber wall, the signal of which is completely absent, the remaining thermocouples are still the value you are looking for deliver maximum engine temperature with sufficient reliability. A rise in temperature, which is the failure of only one measuring point at one critical temperature preceded, only allows for a simple versa close to this measuring point.

Ein weiterer Vorteil der Erfindung ist, daß mit der angegebenen Vorrich­ tung ein einzelner Meß- oder Telemetriekanal zur Überwachung des Trieb­ werks ausreicht. Die Fernübertragung der Meßwerte, wie insbesondere Telemetrie, kann auf gewünschte und bekannte Art und Weise erfolgen.Another advantage of the invention is that with the specified Vorrich device a single measuring or telemetry channel for monitoring the drive works is sufficient. The remote transmission of the measured values, such as in particular Telemetry can be done in a desired and known manner.

Die Werkstoffe für die Thermoelementpaare bzw. Schenkel bzw. Wandungen oder Wandungsteile sind an sich bekannt, z. B. Nickelbasis, wie in der Europäischen Patentschrift 2 67 717 beschrieben oder auf Platinbasis, wie in der Deutschen Offenlegungsschrift 22 04 613 beschrieben oder in anderer bekannter Art und Weise. Auch beschichtete Oberflächen (z. B. aus Platinschicht auf Tantal) ergeben mit Pt-Rhodium-Thermoelementdraht eine Spannung. Die Art der Meßwertfernübertragung und -Auswertung, Verstär­ kung bzw. Vorverstärkung richtet sich nach der Übertragungsstrecke, den zu erwartenden Übertragungsverlusten etc. Bei der elektronischen Auswer­ tung wird die Temperatur digital angezeigt, sonst analog die erzielte Thermospannung (mV). Bevorzugt wird eine Maximalwertschaltung verwendet, d. h. nur eine maximale Spannung soll weitergeleitet werden. Besonders bewährt hat sich die Anwendung eines Filters oder Operationsverstärkers. Zum gleichen Zweck können Dioden in den Thermoelementleitungen angeordnet sein.The materials for the thermocouple pairs or legs or walls or wall parts are known per se, for. B. nickel base, as in the European patent specification 2 67 717 or based on platinum, as described in German Offenlegungsschrift 22 04 613 or in other known way. Also coated surfaces (e.g. made of Platinum layer on tantalum) with Pt rhodium thermocouple wire Tension. The type of remote measurement transmission and evaluation, ampl kung or preamplification depends on the transmission path, the expected transmission losses etc. With the electronic evaluation The temperature is displayed digitally, otherwise the temperature achieved is analog Thermal voltage (mV). A maximum value circuit is preferably used, d. H. only a maximum voltage should be passed on. Especially The use of a filter or operational amplifier has proven itself. For the same purpose, diodes can be used in the Thermocouple lines can be arranged.

Bei einem konkreten Ausführungsbeispiel besteht z. B. die Brennkammerwand aus Pt-Rh 10 und aus gleichem Material der Thermo­ elementedraht mit seiner kalten Lötstelle oder Schweißstelle an der lin­ ken Seite befestigt.In a specific embodiment, there is e.g. B. the combustion chamber wall made of Pt-Rh 10 and made of the same thermo material element wire with its cold soldering or welding point on the lin ken side attached.

Claims (2)

1. Vorrichtung zur Kontrolle der Temperatur von Raketenbrennern während des Betriebs, dadurch gekennzeichnet, daß der Brenner bzw. die Brennkammer wenigstens in einem während des Betriebes hohen Temperaturen ausgesetzten Wandungsbereich aus einem Material besteht, das, oder des­ sen Oberfläche einen Pol oder Schenkel eines Thermoelementes bildet und daß für jede Temperaturmeßstelle auf diesem Wandungsbereich ein Leiter befestigt ist, der mit dem Material des Brenners/der Brennkammer zusam­ mengeschaltet eine Thermospannung zur Auswertung abgibt.1. Device for controlling the temperature of rocket burners during operation, characterized in that the burner or the combustion chamber consists at least in a wall area exposed to high temperatures during operation from a material which, or the surface of which is a pole or leg of a thermocouple forms and that for each temperature measuring point on this wall area, a conductor is attached, which, when connected to the material of the burner / the combustion chamber, emits a thermal voltage for evaluation. 2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß eine Thermospannung durch Fernübertragung zur Auswertung in einem Kontroll­ stand von Raketentriebwerken für bemannte Raumfahrt weitergegeben wird.2. Device according to claim 1, characterized in that a Remote thermal transmission for evaluation in a control was passed on by rocket engines for manned space travel.
DE3838077A 1988-11-10 1988-11-10 Device for monitoring the temperature of rocket burners during operation Expired DE3838077C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE3838077A DE3838077C1 (en) 1988-11-10 1988-11-10 Device for monitoring the temperature of rocket burners during operation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE3838077A DE3838077C1 (en) 1988-11-10 1988-11-10 Device for monitoring the temperature of rocket burners during operation

Publications (1)

Publication Number Publication Date
DE3838077C1 true DE3838077C1 (en) 1989-10-19

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
DE3838077A Expired DE3838077C1 (en) 1988-11-10 1988-11-10 Device for monitoring the temperature of rocket burners during operation

Country Status (1)

Country Link
DE (1) DE3838077C1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0756160A1 (en) * 1995-07-25 1997-01-29 Heraeus Sensor GmbH Temperature measuring device
WO2001061768A1 (en) * 2000-02-18 2001-08-23 Motorola Inc. Thermoelectric power generator for an aircraft
DE102005039828A1 (en) * 2005-08-22 2007-03-08 Endress + Hauser Conducta Gesellschaft für Mess- und Regeltechnik mbH + Co. KG Thermocouple for determination and controlling of temperature of medium is formed in such a manner that thermocouple takes up medium occasionally or thermocouple flows through medium
RU2445503C1 (en) * 2010-10-08 2012-03-20 Открытое акционерное общество "Конструкторское бюро химавтоматики" Test bench for testing power plants with fuel cryogenic components
WO2016166156A1 (en) * 2015-04-16 2016-10-20 Bayerische Motoren Werke Aktiengesellschaft Thermally monitored charging apparatus

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2204613A1 (en) * 1971-02-08 1972-08-24 Johnson Matthey Co Ltd Compensating cable for thermocouples
EP0267717A2 (en) * 1986-11-10 1988-05-18 Nicrobell Pty Limited Thermocouples of enhanced stability

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2204613A1 (en) * 1971-02-08 1972-08-24 Johnson Matthey Co Ltd Compensating cable for thermocouples
EP0267717A2 (en) * 1986-11-10 1988-05-18 Nicrobell Pty Limited Thermocouples of enhanced stability

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0756160A1 (en) * 1995-07-25 1997-01-29 Heraeus Sensor GmbH Temperature measuring device
DE19526975A1 (en) * 1995-07-25 1997-01-30 Heraeus Sensor Gmbh Temperature measuring device
DE19526975C2 (en) * 1995-07-25 1998-02-12 Heraeus Sensor Nite Gmbh Temperature measuring device
WO2001061768A1 (en) * 2000-02-18 2001-08-23 Motorola Inc. Thermoelectric power generator for an aircraft
DE102005039828A1 (en) * 2005-08-22 2007-03-08 Endress + Hauser Conducta Gesellschaft für Mess- und Regeltechnik mbH + Co. KG Thermocouple for determination and controlling of temperature of medium is formed in such a manner that thermocouple takes up medium occasionally or thermocouple flows through medium
RU2445503C1 (en) * 2010-10-08 2012-03-20 Открытое акционерное общество "Конструкторское бюро химавтоматики" Test bench for testing power plants with fuel cryogenic components
WO2016166156A1 (en) * 2015-04-16 2016-10-20 Bayerische Motoren Werke Aktiengesellschaft Thermally monitored charging apparatus
US10259331B2 (en) 2015-04-16 2019-04-16 Bayerische Motoren Werke Aktiengesellschaft Thermally monitored charging device

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Legal Events

Date Code Title Description
8100 Publication of patent without earlier publication of application
D1 Grant (no unexamined application published) patent law 81
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: DEUTSCHE AEROSPACE AG, 8000 MUENCHEN, DE

8327 Change in the person/name/address of the patent owner

Owner name: DAIMLER-BENZ AEROSPACE AKTIENGESELLSCHAFT, 80804 M

8339 Ceased/non-payment of the annual fee