DE10017040A1 - Device for thrust increase of turbojets with regeneration has convergent-divergent nozzle which accelerates bypass flow to supersonic speed - Google Patents

Device for thrust increase of turbojets with regeneration has convergent-divergent nozzle which accelerates bypass flow to supersonic speed

Info

Publication number
DE10017040A1
DE10017040A1 DE2000117040 DE10017040A DE10017040A1 DE 10017040 A1 DE10017040 A1 DE 10017040A1 DE 2000117040 DE2000117040 DE 2000117040 DE 10017040 A DE10017040 A DE 10017040A DE 10017040 A1 DE10017040 A1 DE 10017040A1
Authority
DE
Germany
Prior art keywords
convergent
accelerates
turbojets
regeneration
supersonic speed
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.)
Granted
Application number
DE2000117040
Other languages
German (de)
Other versions
DE10017040C2 (en
Inventor
Christoph Neumann
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.)
NEUMANN, CHRISTOPH, 51515 KUERTEN, DE
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to DE2000117040 priority Critical patent/DE10017040C2/en
Publication of DE10017040A1 publication Critical patent/DE10017040A1/en
Application granted granted Critical
Publication of DE10017040C2 publication Critical patent/DE10017040C2/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • 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
    • F02K3/04—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 the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—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 the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent

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)

Abstract

The device for thrust increase of turbojets with regeneration has a convergent-divergent nozzle which accelerates the bypass flow to supersonic speed.

Description

Bisher bekannte Strahltriebwerke liefern hohen Schub bei relativ niedrigen Geschwindigkeiten, was aus einem großen Massendurchsatz und relativ geringer Austrittsgeschwindigkeit resultiert [ZTL], bzw. eignen sich für hohe Fluggeschwindigkeiten aufgrund hoher Austrittsgeschwindigkeit, liefern aber aufgrund ihres geringen Massendurchsatzes wenig Schub bei kleinen Geschwindigkeiten [TL/ZTL mit sehr kleinem Bypassverhältnis] (Turbine Engines, Handout Part 2, Lufthansa Pilots School BRE OS1/T, März 1999, S. 6-14) Weiter ergibt sich bei den zuletzt angesprochenen Triebwerken in der militärischen Verwendung der Nachteil, dass sie, da sie den größten Teil ihres Schubes aus dem heißen Kreis beziehen, eine auffällige warme Spur ziehen, die mit Infrarotgeräten leicht zu entdecken ist. Aus der vereinfachten Schubgleichung [(Schub = Massendurchsatz (Austrittsgeschwindigkeit - Ein­ trittsgeschwindigkeit)] ergibt sich nun die Notwendigkeit großen Massendurchsatzes und hoher Austrittsgeschwindigkeit für einen größtmöglichen Schub.Previously known jet engines deliver high thrust at relative low speeds, what from a large mass throughput and relatively low exit speed results [ZTL], or are suitable for high flight speeds due to high Exit speed, but deliver due to their low Mass flow little thrust at low speeds [TL / ZTL with very small bypass ratio] (turbine engines, handout Part 2, Lufthansa Pilots School BRE OS1 / T, March 1999, pp. 6-14) Next results in the last mentioned engines in the military use the disadvantage that they, since they are the largest part get their thrust from the hot circle, a striking warm one Draw a track that is easy to discover with infrared devices. From the simplified shear equation [(Thrust = mass flow (exit velocity - on pedaling speed)] there is now a great need Mass throughput and high exit speed for one greatest possible boost.

Dies soll bei dem neuen Triebwerk durch Verwendung eines großen Bypassverhältnisses und Leitung der Mantelstromluft durch eine konvergent-divergente Lavaldüse erreicht werden. Die Luft soll dabei vor dem und im konvergenten Teil der Düse auf einen ausreichend hohen Druck verdichtet und auf Schallgeschwindigkeit beschleunigt werden, was mittels einer, ggf. mehrerer Fanstufen und ggf. eines zusätzlichen überkritischen Fans, als auch durch den konvergenten Querschnittsverlauf der Düse erreicht wird. Im divergenten Teil der Düse wird die Luft unter Druck- und Temperaturabnahme auf Überschallgeschwindigkeit beschleunigt. Da dem heißen Kreis fast die gesamte Energie zum Antrieb des kalten Kreises entzogen wird, sind die Wärmeverluste außerhalb des Triebwerks denkbar gering, wodurch sich guter Gesamtwirkungsgrad ergeben sollte.This is said to be the case with the new engine using a large one Bypass ratio and ducting the sheath flow air through a convergent-divergent Laval nozzle can be achieved. The air should be there the and in the convergent part of the nozzle to a sufficiently high Pressure is compressed and accelerated to the speed of sound, what with one, possibly several fan levels and possibly an additional one supercritical fans, as well as through the convergent Cross-sectional profile of the nozzle is reached. In the divergent part of the nozzle the air will rise under pressure and temperature Accelerated supersonic speed. Since the hot circle almost that all energy for driving the cold circuit is removed Heat losses outside the engine are extremely small, which means that should result in good overall efficiency.

Aufgrund der bei diesem Triebwerk entstandenen Kombination von großem Massendurchsatz und hoher Austrittsgeschwindigkeit wird es möglich, auch schwere Luftfahrzeuge mit hoher Geschwindigkeit bei gleichzeitig großem Startschub zu bewegen. Durch den Hauptanteil kalten Schubes am Gesamtschub wäre dieses Triebwerk auch für militärische Verwendungen sehr geeignet.Because of the combination of it will have a large mass throughput and a high exit speed possible even with heavy aircraft at high speed to move at the same time a big boost. By the main part cold thrust on the total thrust this engine would also be for military uses very suitable.

Claims (1)

Vorrichtung zur Schuberhöhung von Zweikreisturbinenluftstrahltriebwerken, dadurch gekennzeichnet, dass sich hinter der/den Fanstufe/n eine konvergent-divergente Düse befindet, die den Mantelstrom auf Überschall­ geschwindigkeit beschleunigt.Device for increasing the thrust of dual-circuit air jet engines, characterized in that there is a convergent-divergent nozzle behind the fan stage (s), which accelerates the jacket flow to supersonic speed.
DE2000117040 2000-04-05 2000-04-05 Device for increasing the thrust of dual-circuit air jet engines Expired - Fee Related DE10017040C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE2000117040 DE10017040C2 (en) 2000-04-05 2000-04-05 Device for increasing the thrust of dual-circuit air jet engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2000117040 DE10017040C2 (en) 2000-04-05 2000-04-05 Device for increasing the thrust of dual-circuit air jet engines

Publications (2)

Publication Number Publication Date
DE10017040A1 true DE10017040A1 (en) 2001-10-18
DE10017040C2 DE10017040C2 (en) 2003-04-10

Family

ID=7637745

Family Applications (1)

Application Number Title Priority Date Filing Date
DE2000117040 Expired - Fee Related DE10017040C2 (en) 2000-04-05 2000-04-05 Device for increasing the thrust of dual-circuit air jet engines

Country Status (1)

Country Link
DE (1) DE10017040C2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3036422A4 (en) * 2013-08-23 2016-08-17 United Technologies Corp High performance convergent divergent nozzle

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5056738A (en) * 1989-09-07 1991-10-15 General Electric Company Damper assembly for a strut in a jet propulsion engine
US5169288A (en) * 1991-09-06 1992-12-08 General Electric Company Low noise fan assembly

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3036422A4 (en) * 2013-08-23 2016-08-17 United Technologies Corp High performance convergent divergent nozzle
US10550704B2 (en) 2013-08-23 2020-02-04 United Technologies Corporation High performance convergent divergent nozzle

Also Published As

Publication number Publication date
DE10017040C2 (en) 2003-04-10

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Legal Events

Date Code Title Description
OP8 Request for examination as to paragraph 44 patent law
8122 Nonbinding interest in granting licences declared
8304 Grant after examination procedure
8327 Change in the person/name/address of the patent owner

Owner name: NEUMANN, CHRISTOPH, 51515 KUERTEN, DE

8339 Ceased/non-payment of the annual fee