DE854605C - Internal combustion turbine engine for aircraft - Google Patents
Internal combustion turbine engine for aircraftInfo
- Publication number
- DE854605C DE854605C DEK4287D DEK0004287D DE854605C DE 854605 C DE854605 C DE 854605C DE K4287 D DEK4287 D DE K4287D DE K0004287 D DEK0004287 D DE K0004287D DE 854605 C DE854605 C DE 854605C
- Authority
- DE
- Germany
- Prior art keywords
- turbine
- aircraft
- pressure
- compressor
- low
- 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
- 238000002485 combustion reaction Methods 0.000 title claims description 15
- 239000007789 gas Substances 0.000 claims description 7
- 238000010438 heat treatment Methods 0.000 claims description 3
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
Classifications
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
-
- 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
- F02C6/003—Gas-turbine plants with heaters between turbine stages
-
- 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
- F02C6/02—Plural gas-turbine plants having a common power output
-
- 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
- F02C6/20—Adaptations of gas-turbine plants for driving vehicles
- F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Die Erfindung betrifft ein Brennkraftturbinentriebwerk für Flugzeuge mit einer die Luftschraube antreibenden Hochdruck-(Nutzlei,stungs-)Turibine und einer dieser nachgeschalteten Niederdruckturbine, welche die die Arbeitsluft liefernden Verdichter antreibt.The invention relates to an internal combustion turbine engine for aircraft with a high-pressure (utility, power) turibine driving the propeller and one of these downstream low-pressure turbines, which deliver the working air Compressor drives.
Die Möglichkeit der Anwendung von Brennkraftturbinentriebwerken in Flugzeugen hängt von der Anordnung ihrer Komponenten in, der Zelle derartiger Flugzeuge wesentlich ab. Im Falle von: Großflugzeugen für Langstreckendienst spielt der Wirkungsgrad der Brenn@kraftturbine eine große Rolle. In den meisten Fällen bringt die Vergrößerung des Wirkungsgrades eine Erschwernis des Aufbaues mit sich. Luftvorwärmung, Zwischenkühlung und gegebenenfalls Zwischenwärmung erfordern zusätzliche Baugruppen der Brennkraftturbine und vermehren die Leitungen zur Verbindung dieser einzelnen Baugruppen. Eine übersichtliche Anordnung, dem Verwendungszweck en.tsprec'hend, erleichtert die der Brennkraftturbine als Triebwerk für Flugzeuge.The possibility of using internal combustion turbine engines in Aircraft depends on the arrangement of their components in, the airframe of such aircraft significantly. In the case of: large aircraft for long-haul service, the efficiency plays a role the Brenn @kraftturbine plays a major role. In most cases this brings magnification the efficiency makes the construction difficult. Air preheating, intermediate cooling and, if necessary, intermediate heating require additional assemblies of the internal combustion turbine and multiply the lines for connecting these individual assemblies. A clear one Arrangement, appropriate to the intended use, facilitates that of the internal combustion turbine as an engine for aircraft.
Eine derartige Anordnung der Baugruppen eines Brennkraftturbinenrtriebwerkes für Flugzeuge ist Gegenstand der Erfindung. Der Verdichterturbinensatz der Brennkrafttu,rbine ist dabei in zwei oder mehrere nebeneinandergesch:altete, neben der Nutzleistungsturbine in, dem Profil des Flügels angeordnete Sätze unterteilt. Die Achsen sämtlicher Turbinen liegen in Flugrichtung, wobei die Arbeitsluft in den Verdichtersätzen in bezug auf das Flugzeug von vorn nach hinten strqrnt, dort in, Wärmeaustauschern durch die aus den Niederdruckturbinen ausströmenden Gase erhitzt wird und die Brennkammern und die vor diesen liegende Nutzleis,tungsturbine in bezug auf das Flugzeug von hinten. nach vorn durchströmt. Die die Nu.tzleistungsturbine verlassenden Gase durchströmen, gegebenenfalls nach Aufheizung, die Niederdruckturbine in bezug auf das Flugzeug von vorn nach hinten:. Die Verdichtersätze bestehen hierbei ausi einem in bezug auf das Flugzeug vor der Niederdruckturbine liegenden Niederdruckverdichter end einem hinter dieser Turbine liegenden Hochdruckverdichter.Such an arrangement of the assemblies of an internal combustion turbine engine for aircraft is the subject of the invention. The compressor turbine set of the internal combustion engine is in two or more juxtaposed: old ones, next to the power turbine divided into sets arranged in the profile of the wing. The axes of all turbines lie in the direction of flight, with the working air in the compressor units in relation to the aircraft flows from front to back, there in, heat exchangers through the The gases flowing out of the low-pressure turbines are heated and the combustion chambers and the power turbine ahead of these with respect to the aircraft of rear. flows through to the front. The gases leaving the utility power turbine flow through possibly after heating, the low-pressure turbine with respect to the aircraft front to back :. The compressor sets consist of one in relation on the aircraft in front of the low-pressure turbine end low-pressure compressor a high-pressure compressor located behind this turbine.
Die Zeichnung veranschaulicht den Erfindungsgegenstand in schematischer Darstellung. Der Flügel i des Flugzeuges ist durch einen: hohlen Holm 2 in einen vorderen und rückwärtigen Teil unterteilt. Im Bereich der Flügelnase befindet sich die Motorgondel 3. Die Luftschraube 4 wird über ein Getriebe 5, das sich innerhalb der Verkleidung der Motorgondel befindet, von der Nutzleistungsturbine 6 angetrieben. Es ist dies die Hoch.druckurbine der Brennkraftturbinenanlage. Sie wird bei tufschlagt von: Brenngasen, die in den Brennkamzern 7 erhitzt werden. Diese Brennkammern, liegen nmittelbar hinter der Hochdruckturbine und era,Iten die Luft über Leitungen 8 aus zwei regenerativ ler rekuperativ betriebenen Luftvorwärrnern 9, die o dem Flügelholm 2 symmetrisch zur Turbinenihse angeordnet sind. Der Brennstoff wird, durch Düsen io in die Brennkammer eingeführt. Die die Hochdruckturbine 6 verlassenden Gase werden über Leitungen i i in Zwischenbrennkammern 12 geleitet, die mit Einspritzdüsen 13 versehen sind. Nach ihrem Verlassen dieser Brennkammern treten die Gase in die Niederdruckturbinen 14 ein, die symmetrisch zu beiden Seiten der Nutzleistungsturbi:nen und damit Luftschraubenachse angeordnet sind. Nach ihrer Entspannung in diesen Niederdruckturbinen strömen die Abgase über Leitungen 15 in den vorzugsweise im Gegenstrom beaufschlagten Luftvorwärmer 9 und von diesem durch Leitungen 16 über den rückwärtigen Teil des Flügels, entgegengesetzt der Flugrichtung, in die Atmosphäre ab. Die Niederdruckturbinen treiben je einen Niederdruckverdichter 17 und einen Hochdruckverdichter 18 an. Der Eintritt i9 der Niederdruckverdichter hat die Form einer "Fangdüse im Bereich der Flügelnase. Die im Niederdruckverdichter vorverdichtete Luft strömt über eine Leitung 2o in die Zwischenkühler 21 und von diesen über eine Leitung 22 in den Hochdruckverdichter. Nach Weiterverdichtung in diesem wird die Luft in einer Leitung 23 dem Luftvorwärmer zugeführt. Entrittsöffrmngen 24 in der Flügelnase sind für die Kühlluft der Zwischenwärmer vorgesehen.The drawing illustrates the subject matter of the invention in schematic form Depiction. The wing i of the aircraft is through a: hollow spar 2 in one front and rear part divided. In the area of the wing nose there is the motor nacelle 3. The propeller 4 is via a gear 5, which is located within the casing of the motor nacelle, driven by the power turbine 6. It is the high pressure turbine of the internal combustion turbine system. She is at tufschlag from: fuel gases that are heated in the combustion chamber 7. These combustion chambers are located Immediately behind the high-pressure turbine and what, Iten the air via lines 8 two regenerative ler recuperatively operated Luftvorwärrnern 9, the o the wing spar 2 are arranged symmetrically to the turbine sleeve. The fuel is, through nozzles io inserted into the combustion chamber. The gases leaving the high pressure turbine 6 are guided via lines i i into intermediate combustion chambers 12, which are equipped with injection nozzles 13 are provided. After leaving these combustion chambers, the gases enter the low-pressure turbines 14, which are symmetrical on both sides of the power turbines and thus the propeller axis are arranged. After their relaxation in these low-pressure turbines, the flow Exhaust gases via lines 15 into the air preheater, which is preferably acted upon in countercurrent 9 and from this through lines 16 over the rear part of the wing, opposite the direction of flight, into the atmosphere. The low pressure turbines drive one each Low pressure compressor 17 and a high pressure compressor 18. The entry i9 of the The low-pressure compressor has the shape of a "catching nozzle in the area of the wing nose. The Air pre-compressed in the low-pressure compressor flows through a line 2o into the Intercooler 21 and from these via a line 22 into the high-pressure compressor. After further compression in this, the air is in a line 23 to the air preheater fed. Entrittsöffrmngen 24 in the wing nose are for the cooling air of the intermediate heater intended.
Claims (4)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEK4287D DE854605C (en) | 1942-07-29 | 1942-07-29 | Internal combustion turbine engine for aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEK4287D DE854605C (en) | 1942-07-29 | 1942-07-29 | Internal combustion turbine engine for aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
DE854605C true DE854605C (en) | 1952-11-06 |
Family
ID=7210249
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DEK4287D Expired DE854605C (en) | 1942-07-29 | 1942-07-29 | Internal combustion turbine engine for aircraft |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE854605C (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1016504B (en) * | 1953-05-12 | 1957-09-26 | Napier & Son Ltd | Gas turbine engine for aircraft, for example a diesel powered helicopter |
EP1164273A2 (en) * | 2000-06-13 | 2001-12-19 | Rolls-Royce Deutschland Ltd & Co KG | Turbo jet engine with heat exchanger |
WO2022180311A1 (en) * | 2021-02-26 | 2022-09-01 | Psa Automobiles Sa | Turbine engine device with power system generator, and vehicle comprising such a device |
-
1942
- 1942-07-29 DE DEK4287D patent/DE854605C/en not_active Expired
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1016504B (en) * | 1953-05-12 | 1957-09-26 | Napier & Son Ltd | Gas turbine engine for aircraft, for example a diesel powered helicopter |
EP1164273A2 (en) * | 2000-06-13 | 2001-12-19 | Rolls-Royce Deutschland Ltd & Co KG | Turbo jet engine with heat exchanger |
EP1164273A3 (en) * | 2000-06-13 | 2003-10-15 | Rolls-Royce Deutschland Ltd & Co KG | Turbo jet engine with heat exchanger |
US6722119B2 (en) | 2000-06-13 | 2004-04-20 | Rolls-Royce Deutschland Ltd & Co Kg | Turbojet power plant with heat exchanger |
WO2022180311A1 (en) * | 2021-02-26 | 2022-09-01 | Psa Automobiles Sa | Turbine engine device with power system generator, and vehicle comprising such a device |
FR3120251A1 (en) * | 2021-02-26 | 2022-09-02 | Psa Automobiles Sa | TURBOMACHINE DEVICE WITH GENERATOR POWER SYSTEM AND VEHICLE COMPRISING SUCH DEVICE |
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