DE102005044312B3 - Parting plane driving gear for aircraft comprises a valve control unit in the elongation of a valve shaft and operated by a connecting rod with a row of actuating plungers - Google Patents
Parting plane driving gear for aircraft comprises a valve control unit in the elongation of a valve shaft and operated by a connecting rod with a row of actuating plungers Download PDFInfo
- Publication number
- DE102005044312B3 DE102005044312B3 DE200510044312 DE102005044312A DE102005044312B3 DE 102005044312 B3 DE102005044312 B3 DE 102005044312B3 DE 200510044312 DE200510044312 DE 200510044312 DE 102005044312 A DE102005044312 A DE 102005044312A DE 102005044312 B3 DE102005044312 B3 DE 102005044312B3
- Authority
- DE
- Germany
- Prior art keywords
- gas jet
- turbocharger
- valve
- engine according
- gas
- 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 - Fee Related
Links
- 239000011230 binding agent Substances 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 5
- 238000000926 separation method Methods 0.000 claims description 5
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 claims 1
- 238000002485 combustion reaction Methods 0.000 description 8
- 239000000446 fuel Substances 0.000 description 4
- 229910001209 Low-carbon steel Inorganic materials 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 241000251730 Chondrichthyes Species 0.000 description 1
- 229910000737 Duralumin Inorganic materials 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000012384 transportation and delivery Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
-
- 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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
-
- 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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
- F02C5/10—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
-
- 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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
- F02C5/12—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/711—Shape curved convex
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/712—Shape curved concave
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
Description
Eine Alternative für Propellerturbine soll das Trennflächentriebwerk sein. Es zeichnet sich aus durch Anwendung von Strömungstechnik. Grundlage hierfür ist die Nutzung der Naturerscheinungen: Luftzähigkeit und Trennflächendruckabfall.A alternative for Propeller turbine is said to be the interface engine. It draws characterized by application of flow technology. Basis for this is the use of natural phenomena: air toughness and interface pressure drop.
Trennflächendruckabfall wird erzeugt durch einen Gasstrahl in beidendig offenem Triebwerksgehäuse. Durchdringt der Gasstrahl den Luftraum des Triebwerksgehäuses, so fällt der Luftdruck ab auf an Vakuum grenzenden Zustand.Interface pressure drop is generated by a gas jet in both open engine housing. penetrates the gas jet the airspace of the engine housing, so the air pressure drops to a vacuum bordering state.
Eine weitere Naturerscheinung, „horror vacui", läßt solchen Zustand nicht zu und sorgt für schnellsten Ausgleich. Der Ausgleichskraft entgegenwirkt Luftzähigkeit; bei deren Überwindung entsteht diejenige Zugkraftkomponente, die das Flugzeug antreibt.A another natural phenomenon, "horror vacui ", lets such State not to and ensures the fastest Compensation. The balancing force counteracts air toughness; in overcoming them arises that tractive force component that drives the aircraft.
Als
Stand der Technik seien die Druckschriften
Die Gasstrahldruckvorlage entsteht durch pulsierende Kraftstoffverbrennungen in einer Reihe von verschließbaren Brennkammern. Das entstandene und freigesetzte Gas wird in einer Ringspaltdüse zum hohlen Gasstrahl geformt. Nach Verlassen der Ringspaltdüse verursacht der frei fliegende Gasstrahl beim Durchdringen des Luftstromes im Triebwerksgehäuse den beabsichtigten Druckabfall.The Gas jet pressure produced by pulsating fuel burns in a series of lockable Combustion chambers. The resulting and released gas is in a Annular gap nozzle for hollow gas jet shaped. After leaving the annular gap nozzle caused the freely flying gas jet when penetrating the air flow in Engine casing the intended pressure drop.
Erforderlich für die Triebwerksfunktion ist die Formstabilität des Gasstrahles. Zu deren weitgehenden Erhalt ist im Kernbereich der Gasstrahlmasse in vorgegebener Länge ein Gasstrahlformbinder aus zwei eng zueinander stehenden Blechschalen eingefügt. Die beiden sich gegenüber stehenden Blechschalen sind spiegelbildlich gleich geformt.Required for the Engine function is the dimensional stability of the gas jet. To whose extensive conservation is in the core area of the gas jet mass in given Length one Gas jet binder consisting of two closely spaced sheet metal shells inserted. The two opposite each other standing sheet metal shells are the same shape as a mirror image.
Um der Ringspaltdüse die Form einer Lavaldüse zu geben, trägt der Gasstrahlformbinder an erforderlicher Stelle konvexe Ausbuchtung.Around the annular gap nozzle the shape of a Laval nozzle to give, carries the gas jet binder at the required point convex bulge.
Außerhalb der Ringspaltdüse dient dann der Gasstrahlformbinder dem Zusammenhalt des Gasstrahles, indem die Blechschalen konkave Kontur annehmen. Die ruhende Hohlform soll den mit hoher Geschwindigkeit entlangstreichenden Gasstrahl nach innen zusammenziehen. Die dazu erforderliche Zugkraftkomponente quer zur Strömung entsteht durch eine Art innere Trennfläche zwischen Grenzschicht und Gasstrahl. Der dadurch bedingte innere Druckabfall ermöglicht auf diese Weise den Erhalt der Gasstrahlform.Outside the annular gap nozzle then the gas jet mold binder serves the cohesion of the gas jet, by the metal shells accept concave contour. The resting mold is intended to relieve the high velocity gas jet contract inside. The required traction component across the flow arises through a kind of inner interface between boundary layer and Gas jet. The resulting internal pressure drop allows up this way preserving the gas jet shape.
Zur Verringerung der Wirbelbildung auf den Grenzschichten kann beispielsweise die Oberflächenstruktur von Haifischhaut angewendet und auf dem Gasstrahlformbinder geprägt werden.to Reduction of vortex formation on the boundary layers can be, for example the surface structure applied by shark skin and embossed on the gas jet binder.
Die Größe der Trennfläche richtet sich nach der vorgegebenen Triebwerksleistung.The Size of the interface according to the given engine power.
Näherungsweise Ermittlung der erforderlichen Trennflächengröße kann mit der aktiven Kreisringfläche der Luftschraube eines gleich starken Triebwerks verglichen werden.Approximately Determining the required interface size can be done with the active annulus of the Propeller of an equally powerful engine.
Ein Ausführungsbeispiel der Erfindung wird nachfolgend anhand der Zeichnung näher erläutert. In dieser zeigen:One embodiment The invention will be explained in more detail with reference to the drawing. In show this:
Vorgestellt wird in Folgendem ein Trennflächentriebwerk mit 566 kW (770 PS) Startleistung.Presented in the following becomes a separation area engine with 566 kW (770 hp) take-off power.
Bei
paarweisem Einsatz wäre
es geeignet für Regionalverkehrsflugzeug
DO 228, mit 19 Fluggästen
und 700 m Startstrecke.
Reisegeschwindigkeit nach Umrüstung ca.
750 km/h.For pairwise use, it would be suitable for regional airliner DO 228, with 19 passengers and 700 m take-off.
Cruising speed after conversion approx. 750 km / h.
Auf Zeichnung 1:On drawing 1:
Anwendungsbeispiel vom Trennflächentriebwerk in vier Arbeitsbereichen.Application example of Interface engine in four workspaces.
1) Arbeitsbereich Druckabfallzone, ist unmittelbar zuständig für Startleistung.1) working range pressure drop zone, is directly responsible for takeoff performance.
-
Pos.
1 : Trennfläche, 4,55 m2 Trennfläche ist der mehr oder weniger scharf begrenzte Geschwindigkeitsübergang zwischen zwei unterschiedlich schnell strömend gasförmigen Medien.Pos.1 : Separation surface, 4.55 m 2 separation surface is the more or less sharply defined velocity transition between two different rapidly flowing gaseous media. -
Pos.
2 : Gasstrahl, 825 m/s Dargestellter Gasstrahl ist rohrförmig gestaltet, um seine Oberfläche (Trennfläche) zu vergrößern.Pos.2 : Gas jet, 825 m / s Illustrated gas jet is tubular designed to increase its surface area (separation surface). -
Pos.
3 : Gasstrahlformbinder aus zwei gegenüberstehenden Blechschalen.Pos.3 : Gas jet binder from two opposite sheet metal shells. -
Pos.
4 : RandluftstromPos.4 : Edge airflow -
Pos.
5 : KernluftstromPos.5 : Core airflow
2) Arbeitsbereich Gasstrahlerzeuger2) Work area gas jet generator
-
Pos.
6 : Ringspaltdüse aus KeramikPos.6 : Ceramic annular gap nozzle -
Pos.
7 : Brennkammer, 15 Stück insgesamt Verdichtungsraum 8346 cm3, Adiabatische Aufladung mit Verdichtungsverhältnis ε = 5, Isochorische Kraftstoffverbrennung bis 31,7 bar bei 911°C, Dreitaktarbeitsweise: je Takt 0,02 sek, Taktfolge 16,66Pos.7 Combustion chamber, 15 units total compression chamber 8346 cm 3 , adiabatic charge with compression ratio ε = 5, isochoric fuel combustion up to 31.7 bar at 911 ° C, three-stroke mode: 0.02 sec per cycle, clock rate 16.66 -
Pos.
8 : Auslaßventilschieber Öffnungsdruck: 63,7 kg, Ventilteller ⌀ 1,6 cm, je Brennkammer 6 Stück. Ventilsteuerung mittels hydraulischem Kraftübersetzer 1:8, durch Verlängerung des Ventilschaftes auf Schubstange in Reihe sitzender 6 Arbeitskolben in Einzelkammern mit je 8 bar Hydraulikanschluß.Pos.8th : Outlet valve spool Opening pressure: 63.7 kg, valve disk ⌀ 1.6 cm, per combustion chamber 6 pieces. Valve control by means of hydraulic power booster 1: 8, by extension of the valve stem on push rod in series sitting 6 working pistons in single chambers with 8 bar hydraulic connection. -
Pos.
9 : Einlaßventilschieber: Ventilteller ⌀ 2 cm; je Brennkammer 3 EinlaßventilePos.9 : Inlet valve spool: valve plate ⌀ 2 cm; each combustion chamber 3 intake valves
3) Arbeitsbereich Funktionsvernetzung3) workspace functional networking
-
Pos.
10 : Funktionverteiler für Brennkammern Verteilergerät nach Art des üblichen Zündverteilers mit berührungsfreier Schaltung im Kraftfahrzeug, Schaltschritte alle 0,02 sek. Brennkammer: Aufladen einschließlich Kraftstoff einspritzen, schließen und zünden; Brennkammer entladen. Ausführung der Steuerungsanlage mit Einbauelementen von Leistungstransistoren. Pumpenanlagen für Kraftstofförderung und Einspritzung, Herstellung von Hydrauliköldruck und Schmierölkreislauf.Pos.10 : Function distributor for combustion chambers Distributor device in the manner of the usual ignition distributor with non-contact switching in the motor vehicle, switching steps every 0.02 sec. Combustion chamber: Charging including fuel injecting, closing and igniting; Discharge combustion chamber. Design of the control system with built-in elements of power transistors. Pumping equipment for fuel delivery and injection, production of hydraulic oil pressure and lubricating oil circuit.
4) Arbeitsbereich Leistungszentrale4) Work area power center
-
Pos.
11 : Triebwerksgenerator: Eindruckgasturbine, Gasdruckanschluß 30 bar, 142,8 kW (193 PS), ⌀ 1,08 m, 6000 1/min.Pos.11 : Engine generator: Impression gas turbine, gas pressure connection 30 bar, 142,8 kW (193 hp), ⌀ 1,08 m, 6000 1 / min. -
Pos.
12 : Turbolader: Vierstufiges Einscheibenschleudergebläse Fördermenge 339 Ltr./s, 8 bar, ⌀ 1,08 m, n = 6000 1/min, 96,2 kW (130 PS) Verbindungswelle zwischen Triebwerksgenerator und Turbolader ⌀ 200 mm in Schichtbauweise: außen aus Flußstahl mit Keilwellenprofil; Zwischenschicht aus Duraluminium nach der Mitte zu unterbrochen; dritte Schicht nach den Enden zu Lagerzapfen aus Flußstahl ebenfalls in Rohrform.Pos.12 : Turbocharger: Four-stage single-disc centrifugal blower Flow rate 339 ltr./s, 8 bar, ⌀ 1.08 m, n = 6000 rpm, 96.2 kW (130 hp) Connecting shaft between engine generator and turbocharger ⌀ 200 mm in layered construction: outer made of mild steel with splined shaft profile; Intermediate layer of duralumin after the middle to interrupted; third layer after the ends to bearing pins made of mild steel also in tube form. -
Pos.
13 : Stromversorger: Dynamomaschine 46,6 kW (63 PS), n = 600 1/minPos.13 : Electricity supplier: dynamo 46,6 kW (63 hp), n = 600 1 / min
Claims (6)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200510044312 DE102005044312B3 (en) | 2005-09-16 | 2005-09-16 | Parting plane driving gear for aircraft comprises a valve control unit in the elongation of a valve shaft and operated by a connecting rod with a row of actuating plungers |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200510044312 DE102005044312B3 (en) | 2005-09-16 | 2005-09-16 | Parting plane driving gear for aircraft comprises a valve control unit in the elongation of a valve shaft and operated by a connecting rod with a row of actuating plungers |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102005044312B3 true DE102005044312B3 (en) | 2007-01-11 |
Family
ID=37562784
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE200510044312 Expired - Fee Related DE102005044312B3 (en) | 2005-09-16 | 2005-09-16 | Parting plane driving gear for aircraft comprises a valve control unit in the elongation of a valve shaft and operated by a connecting rod with a row of actuating plungers |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE102005044312B3 (en) |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR636026A (en) * | 1927-06-15 | 1928-03-30 | Turbo-compression thruster | |
GB781482A (en) * | 1954-09-10 | 1957-08-21 | Lemuel Pon | Gas turbine engine |
DE1045732B (en) * | 1952-12-19 | 1958-12-04 | Schmidt Paul | Device for generating thermal and mechanical energy by intermittently repeated combustion of ignitable mixture |
US3088276A (en) * | 1959-08-31 | 1963-05-07 | Hudson Perry David | Combustion products pressure generator |
-
2005
- 2005-09-16 DE DE200510044312 patent/DE102005044312B3/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR636026A (en) * | 1927-06-15 | 1928-03-30 | Turbo-compression thruster | |
DE1045732B (en) * | 1952-12-19 | 1958-12-04 | Schmidt Paul | Device for generating thermal and mechanical energy by intermittently repeated combustion of ignitable mixture |
GB781482A (en) * | 1954-09-10 | 1957-08-21 | Lemuel Pon | Gas turbine engine |
US3088276A (en) * | 1959-08-31 | 1963-05-07 | Hudson Perry David | Combustion products pressure generator |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
8100 | Publication of the examined application without publication of unexamined application | ||
8364 | No opposition during term of opposition | ||
R119 | Application deemed withdrawn, or ip right lapsed, due to non-payment of renewal fee |