WO2012097797A2 - Échangeur thermique et moteur à réaction comportant un tel échangeur thermique - Google Patents

Échangeur thermique et moteur à réaction comportant un tel échangeur thermique Download PDF

Info

Publication number
WO2012097797A2
WO2012097797A2 PCT/DE2012/000031 DE2012000031W WO2012097797A2 WO 2012097797 A2 WO2012097797 A2 WO 2012097797A2 DE 2012000031 W DE2012000031 W DE 2012000031W WO 2012097797 A2 WO2012097797 A2 WO 2012097797A2
Authority
WO
WIPO (PCT)
Prior art keywords
flow
heat exchanger
jet engine
heat exchange
mixer
Prior art date
Application number
PCT/DE2012/000031
Other languages
German (de)
English (en)
Other versions
WO2012097797A3 (fr
Inventor
Stefan NEUHÄUSLER
Wilhelm Satzger
Siegfried Sikorski
Karl-Heinz Dusel
Roland Huttner
Hans-Christian Melzer
Erwin Bayer
Original Assignee
Mtu Aero Engines Gmbh
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 Mtu Aero Engines Gmbh filed Critical Mtu Aero Engines Gmbh
Publication of WO2012097797A2 publication Critical patent/WO2012097797A2/fr
Publication of WO2012097797A3 publication Critical patent/WO2012097797A3/fr

Links

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • 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
    • 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
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/115—Heating the by-pass flow by means of indirect heat exchange
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • 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
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency
    • 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

Definitions

  • the invention relates to a heat exchanger, in particular for a jet engine, and a jet engine with at least one heat exchanger.
  • the exhaust gas heat exchanger is a lancet frame temperature exchanger, as is known per se from the prior art. The installation of such heat exchangers in the
  • EP 1 589 204 A2 discloses an exhaust gas heat exchanger in the exhaust gas jet of a
  • FIGS. 3A and 3B show one end of a flower mixer, wherein FIG. 3A is a longitudinal sectional view and FIG.
  • FIG. 3B is a cross-sectional view along an arrow indicated in FIG. 3A by a dashed and dotted line BB in the direction of view.
  • the prior art engine 110 includes a shell 111 within which a central main flow channel 112 and a shell-shaped bypass channel 114 extend.
  • a so-called flower mixer 117 is arranged in the rear region of the engine 1 10 .
  • the flower mixer is a tubular member, the downstream end is more and more curled, so that the tube end a
  • the pipe wall thus forms outer channels 117 a and
  • Inner channels 117b off.
  • main and sub-streams downstream of the pipe end in a mixing zone 150 mix more uniformly, and the guiding action of the inner channels 117b additionally causes a reduction in a twist of the core flow (the main stream).
  • Object of the present invention is an improved heat exchanger, in particular for use in a jet engine, an improved flow mixer and a
  • the present invention is based on the consideration that the manufacturing and
  • Assembly effort of a jet engine can be reduced if structural and / or fluid mechanical functions, ie functions of structural and or fluidmechani see elements with which a heat exchanger are combined, ie if a heat exchanger as a structural and / or fluid mechanical element or integral with a , Such is formed or vice versa, and at the same time, preferably, the entire component is produced generatively.
  • a heat exchanger in particular for a jet engine, as a structural and / or fluid mechanical element or integrally formed with such and produced at least partially generative.
  • Aspect of the invention is a structural and / or fluid mechanical element for a Turbomachine, in particular for a jet engine, as one or integrally formed with a heat exchanger and at least partially produced generatively.
  • a structural mechanical element is understood as meaning, in particular, a component which (also) contributes to the mechanical load bearing capacity of a structure which does not have to belong to the heat exchanger per se functionally.
  • a fluid-mechanical element is to be understood as meaning a component which (also) contributes to the flow-guiding property of a structure which is not functionally equivalent to the structure
  • Heat exchanger must belong to.
  • a heat exchanger structure fulfills a double or multiple function within an engine. Due to the
  • heat exchanger function and structural and / or fluid mechanical function within an engine, without having to add pipes or plates or other heat exchange elements. Therefore, the possibility of leaks, which may occur at joints, can be reduced or avoided altogether, which can also reduce the testing costs for such a component.
  • the heat exchanger can be easily adapted as an integrated component with optimal space utilization and location to a space present in a flow channel.
  • the heat exchanger is flowed through by a heat exchange medium and has at least one heat exchange section, which can be flowed around by a fluid flow, wherein the heat exchange section has one or more lamellae, lancets, tubes or plates. Further preferably, the heat exchanger is designed so that the
  • Heat exchange portion is flowed through by the heat exchange medium.
  • the heat exchanger is designed such that the heat exchange section has a surface topography, which is designed in terms of a high heat transfer and a low flow resistance, in particular with respect to the flowing around fluid stream.
  • the heat exchanger is configured such that the fluid flow is a secondary flow or a part of a secondary flow of a jet engine, wherein the heat exchange medium a Main stream of the jet engine between compressor stages, in particular between a low or medium pressure compressor stage and a medium or high pressure compressor stage of the jet engine, is taken, wherein preferably the entire main flow of
  • Jet engine optionally divided into partial streams, by the or
  • Heat exchange sections is conductive, and a next compressor stage is fed again.
  • a removal can be understood according to the above definition in particular the removal of a partial flow, but also a deflection of the total flow (each of the main flow).
  • an intercooler for a compressor of a jet engine can be advantageously realized.
  • the heat exchanger is configured such that the fluid flow is a main flow of a jet engine after a turbine stage, in particular a last turbine stage of
  • Jet engine, and the heat exchange medium is at least a partial flow of the main flow of the jet engine, after a compressor stage, in particular a last
  • High-pressure compressor stage of the jet engine is removed, and after flowing through the heat exchange portion, preferably the main stream before or in the region of
  • Removal can be understood as meaning both the removal of a partial flow and a deflection of the total flow (in each case of the main flow). With this configuration can also be a recuperative
  • Combustion air can be advantageously realized.
  • the heat exchanger is integrally formed with a mixer, which the
  • the mixer is designed as a flower mixer, wherein heat exchange sections are arranged in flowed through by the main stream of the jet engine areas.
  • the design as a flower mixer has proven to be a simple and effective interpretation possibility.
  • the heat exchanger is formed integrally with a support structure. This can improve the degree of integration, the design flexibility, the versatility and the ease of installation.
  • the heat exchanger is made in several sections, wherein flow-through cavities of heat exchange sections do not extend over a plurality of sections.
  • portions may be provided which are composable in the circumferential direction.
  • a jet engine with at least one heat exchanger or at least one structural and / or fluid mechanical element as described above is provided.
  • a flow mixing device for mixing a first gas flow with a second gas ström, wherein the flow mixing device comprises a plurality of first flow channels for guiding at least a partial flow of the first gas flow and a plurality of second
  • Flow channels for guiding at least a partial flow of the second gas stream, wherein at least in a part of the first flow channels and / or the second
  • Fig. 1 is a downstream portion of an engine with integrated mixer
  • FIG. 2 shows an upstream portion of an engine with integrated support web and heat exchanger in a schematic longitudinal sectional view of a secondstrasbei game of the present invention.
  • FIG. 3A is a schematic longitudinal sectional view of a downstream portion of a prior art flower mixer;
  • Fig. 3B is a cross-sectional view taken along a line B-B in Fig. 3A.
  • FIGS. 1 and 2 described two basic embodiments of the invention.
  • Fig. 1 is a schematic longitudinal sectional view showing a downstream portion of a jet engine 10 as a first embodiment of the present invention.
  • a main flow channel 12 extend with a main flow
  • the engine 10 in the upstream region of the main flow channel 12 as a core engine at least one compressor assembly, a
  • the main flow 13 is as exhaust gas flow of
  • the main flow channel 12 and the bypass channel 14 are through an insulating member
  • Partition wall 16 separated from each other.
  • a flow mixer 17 is connected to the insulating member 16.
  • the flow mixer 17 has a circular cross-section at an upstream end, which waves more and more like a flower in the downstream direction to form inner and outer channels similar or similar to those known per se in Fig. 3B. Furthermore, a centrally located
  • Deflection cone 18 is provided, which urges the core flow 13 in the region near the axis radially outward. Through the deflection cone 18 and the inner contour of the flow mixer 17, a flow cross section 19 for the core flow 13 is defined.
  • Heat exchanger 20 is arranged. In the figure, only a portion of the heat exchanger 20 is visible, which fits in an inner channel of the flow mixer 17 (see Fig. 17b in Fig. 3B). It should be noted that the heat exchanger 20 covers the entire area through which the core flow 13 flows.
  • the heat exchanger 20 is a so-called lancet heat exchanger in which a plurality of tubes 21 having a lancet-like (approximately elliptical) cross-section
  • the tubes (lancets) 21 are approximately horseshoe-shaped or U-shaped from the flow distributor to the return manifold.
  • the flow distributor 21a is connected to a supply line 22, and the return distributor 21b is connected to a return line 24; the connection is made via a common flange 20 a of the heat exchanger 20.
  • the lancets 21 are flowed around during operation by the (hot) core flow 13.
  • Supply line 22 leads from a point downstream of a last compressor stage (not shown) of the engine 10 branched compressor air 23 to the heat exchanger, and the return line 24 leads the heated in the lancets 21 by the hot core flow 13 air as combustion air 25 to the combustion chamber (not shown ) back.
  • the heat exchanger 20 is formed as an integral component with the flow mixer (flower mixer) 17.
  • the formation of this integral component (hereinafter referred to as
  • RM method is a collective term for stratified original form method in which a geometric, three-dimensional body in layers by means of
  • RM methods which are also known as stereo lithographic mastering, build-up welding, laser generation or
  • the integral design together with the generative manufacturing process, makes it possible to design the junctions of the manifolds (conduits) to the lancets 21, which are conventionally glued, soldered or welded, for example, as joint-free transitions Due to the layered structure, it is also possible to design the surface topography in such a way that on the one hand the heat transfer is optimized, without on the other side the
  • the flow mixer 17 may be formed integrally with the insulating member 16 or a part thereof, and the heat exchanger 20 may be formed integrally with the insulating member 16
  • Lines 22, 24 or a part thereof may be formed.
  • the heat exchanger 20 can be formed integrally with the deflection cone 18 instead of the flower mixer 17.
  • the mixer / heat exchanger 17, 20 is divided into segments circumferentially to facilitate assembly within the engine 10. This extend
  • a segment may comprise several flowers.
  • a mixer / heat exchanger 17, 20 may be divided into two halves, four quarters, or as many segments as there are flowers.
  • the parting planes are in the region of the outer channels of the flower mixer (compare 117a in Fig. 3B).
  • the portions of the heat exchanger 20 disposed within an internal passage of the flower mixer 17 may in turn be divided without conduits, channels or lancets. to cut; In this case, the dividing planes may be in the range of
  • Inner channels or in the region of the heat exchanger 20 are, which can give the joints of the segments higher stability.
  • FIG. 2 shows in a schematic longitudinal sectional view of an upstream portion of a jet engine 10 as a second Auasflihrungsbei game of the present invention.
  • a main flow channel 12 Within a drive gondola 1 1 run a main flow channel 12 with a main flow
  • the illustrated area comprises a compressor arrangement with a multi-stage
  • combustion chamber and a turbine assembly are provided downstream of the high-pressure compressor, as it in itself in literature and practice in manifold
  • Intercooler 30 is arranged.
  • the intercooler 30 has a flow channel 31, which extends in the region of the sheath flow 15 and a plurality of cooling fins (not shown), which extend into the secondary flow 15.
  • the flow channel 31 biases a transverse or diagonal to the flow direction of the sheath flow 15 lying
  • a support bar 34 connects the
  • the heat exchanger 30 is formed as an integral part with the support web 34.
  • the formation of this integral component (hereinafter referred to as mixer / heat exchanger) is carried out by the RM method explained above (for "rapid manufacturing").
  • the advantages of the integral, generative design correspond analogously to those mentioned in connection with the heat exchanger 20 of the first exemplary embodiment. Joints, joints and mounting points can be largely avoided. Leakage due to
  • Intercooler 30 to adapt to the geometry of the bypass channel and the main flow channel.
  • intercooler 30 and support bar 34 allows a
  • the resulting component performs a dual function as a heat exchanger and structural component or fluid mechanical component of the engine.
  • the intercooler 30 extracts heat from the compressor air.
  • the air from the low pressure compressor 26 is cooled and supplied to the high pressure compressor 28, which is the improves thermal efficiency and reduces the thermal load of the high-pressure compressor 28.
  • the Volunteerstromlufl 15 is preheated, which increases the efficiency of the mixer. Thus, a reduction of the noise and an increase in the overall efficiency can be achieved.
  • the ribs of the intercooler 30 are connected to a housing (not shown in detail).
  • the support structure is hollow, optionally thin-walled and / or profiled, which can also reduce the weight and can be realized advantageously with the RM method.
  • the support structure is executed segmented.
  • the intercooler 30 may, if appropriate according to the number of segments, divided into several parts (rings), for example, from central, common flanges (not shown in detail) extend from. A segmented design can also simplify the assembly work and the adaptation to the geometry of the nacelle 11.
  • the intercooler 30 is as
  • Compressor medium pressure compressor
  • an intercooler between medium and high pressure compressor, between low and medium pressure compressor or both may be provided.
  • the heat exchanger 20 and the intercooler 30 are heat exchangers or
  • the flow mixer 17 and the Support web 34 are structural and / or fluid mechanical elements in the context of the invention.
  • the flow mixer 17 is also a flow mixing device according to the invention.
  • Exemplary embodiments are heat exchanger media in the sense of the invention.
  • the lancets 21 in the first embodiment and the shelves 32 with transverse ribs and the cooling fins, in part also the flow channel 31 itself, are heat exchange sections in the context of the invention.
  • the core flow 13 in the first embodiment and the secondary flow 15 in the second embodiment are flowing fluid flows in the sense of the invention.
  • the main flow 13 and the secondary flow 15 of the first embodiment are first and second gas streams according to the invention, and inner and outer channels of the flow mixer 17 are first and second flow channels in the context of the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Abstract

L'invention concerne un échangeur thermique notamment destiné à un moteur à réaction, conçu en tant qu'élément structural ou à mécanique des fluides, ou conçu d'un seul tenant avec un tel élément, l'échangeur thermique étant fabriqué au moins partiellement de façon générative.
PCT/DE2012/000031 2011-01-18 2012-01-16 Échangeur thermique et moteur à réaction comportant un tel échangeur thermique WO2012097797A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011008773A DE102011008773A1 (de) 2011-01-18 2011-01-18 Wärmetauscher und Strahltriebwerk mit solchem
DE102011008773.7 2011-01-18

Publications (2)

Publication Number Publication Date
WO2012097797A2 true WO2012097797A2 (fr) 2012-07-26
WO2012097797A3 WO2012097797A3 (fr) 2012-11-15

Family

ID=45999501

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2012/000031 WO2012097797A2 (fr) 2011-01-18 2012-01-16 Échangeur thermique et moteur à réaction comportant un tel échangeur thermique

Country Status (2)

Country Link
DE (1) DE102011008773A1 (fr)
WO (1) WO2012097797A2 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015204014A1 (de) * 2015-03-05 2016-09-08 Mahle International Gmbh Wärmetauscher, insbesondere für ein Kraftfahrzeug
CN107538006B (zh) * 2017-05-18 2023-05-23 西南石油大学 一种用于节流阀的硬质合金阀芯的加工装置及方法
DE102022115588A1 (de) 2022-06-10 2023-12-21 MTU Aero Engines AG Wärmetauscher für eine hohe Anströmgeschwindigkeit

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2575683A (en) * 1947-01-13 1951-11-20 Lockheed Aircraft Corp Intercooler and control system for turbo power plants
US3267673A (en) * 1965-10-22 1966-08-23 Gen Electric Recuperator for gas turbine powerplants
US5832715A (en) * 1990-02-28 1998-11-10 Dev; Sudarshan Paul Small gas turbine engine having enhanced fuel economy
DE19740502A1 (de) * 1997-09-15 1999-03-18 Fraunhofer Ges Forschung Verfahren zur Herstellung von Bauteilen mit einem oberflächennahen Durchfluß- und Verteilungssystem für Flüssigkeiten und/oder Gase
US6134880A (en) * 1997-12-31 2000-10-24 Concepts Eti, Inc. Turbine engine with intercooler in bypass air passage
DE102006021436A1 (de) * 2006-05-09 2007-11-15 Mtu Aero Engines Gmbh Gasturbinentriebwerk

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3903713A1 (de) 1989-02-08 1990-08-09 Mtu Muenchen Gmbh Strahltriebwerk
US7254937B2 (en) 2004-04-21 2007-08-14 General Electric Company Gas turbine heat exchanger assembly and method for fabricating same
US7866372B2 (en) 2006-12-20 2011-01-11 The Boeing Company Method of making a heat exchanger core component
DE102007004741A1 (de) 2007-01-31 2008-08-07 Mtu Aero Engines Gmbh Gasturbine mit einem Nachleitkranz und mit einem Mischer
DE102008023816A1 (de) 2008-05-15 2009-11-19 Mtu Aero Engines Gmbh Mischdüsenaufbau

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2575683A (en) * 1947-01-13 1951-11-20 Lockheed Aircraft Corp Intercooler and control system for turbo power plants
US3267673A (en) * 1965-10-22 1966-08-23 Gen Electric Recuperator for gas turbine powerplants
US5832715A (en) * 1990-02-28 1998-11-10 Dev; Sudarshan Paul Small gas turbine engine having enhanced fuel economy
DE19740502A1 (de) * 1997-09-15 1999-03-18 Fraunhofer Ges Forschung Verfahren zur Herstellung von Bauteilen mit einem oberflächennahen Durchfluß- und Verteilungssystem für Flüssigkeiten und/oder Gase
US6134880A (en) * 1997-12-31 2000-10-24 Concepts Eti, Inc. Turbine engine with intercooler in bypass air passage
DE102006021436A1 (de) * 2006-05-09 2007-11-15 Mtu Aero Engines Gmbh Gasturbinentriebwerk

Also Published As

Publication number Publication date
DE102011008773A1 (de) 2012-07-19
WO2012097797A3 (fr) 2012-11-15

Similar Documents

Publication Publication Date Title
DE112009000753B4 (de) Einheitliche Leitung zur Beförderung von Fluiden
EP2010773B1 (fr) Aube de turbine
EP0125572B1 (fr) Brûleur polycombustible
EP3077751B1 (fr) Échangeur de chaleur et procédé de fabrication d'un échangeur de chaleur
DE102014111844A1 (de) Verfahren und System zur Schaffung einer Kühlung für Turbinenkomponenten
DE112020000789B4 (de) Hochtemperaturbauteil und verfahren zur herstellung des hochtemperaturbauteils
WO2006048401A1 (fr) Etage de turbine optimise dans une installation de turbines et procede de conception
EP2204628A1 (fr) Échangeur de chaleur en plastique
EP3585509A1 (fr) Échangeur thermique et réacteur
EP3526519A1 (fr) Pointe de brûleur comprenant un système de conduit d'air et un système de conduit de combustible pour un brûleur et procédé de fabrication associé
WO2014146795A1 (fr) Récupérateur à faisceaux de tubes sur un four de frittage, et procédé de transfert de chaleur au moyen d'un four de frittage et d'un récupérateur à faisceaux de tubes
WO2012097797A2 (fr) Échangeur thermique et moteur à réaction comportant un tel échangeur thermique
WO2010127748A1 (fr) Dispositif de guidage des gaz d'échappement destiné à un moteur à combustion interne doté d'un générateur thermoélectrique
DE3813202A1 (de) Waermetauscher
DE102015102311A1 (de) Rohrbündelwärmeübertrager
DE102017200643A1 (de) Brennerspitze mit einer Luftkanalstruktur und einer Brennstoffkanalstruktur für einen Brenner und Verfahren zur Herstellung der Brennerspitze
EP2914822B1 (fr) Système d'échappement avec générateur thermoélectrique
DE602004001808T2 (de) Brennkammer eines Raketenantriebs
WO2014127964A1 (fr) Élément de transfert thermique
DE102022209830A1 (de) Übergangsstück, Brennkammer und Gasturbinenmotor
DE102010032324A1 (de) Wärmetauscher, Anordnung von Wärmetauschern sowie Gasturbinentriebwerk mit Wärmetauscher oder Anordnung solcher
EP2585684A1 (fr) Turbine à vapeur à une carcasse avec surchauffe intermédiaire
DE3147647A1 (de) "verfahren zur herstellung von hohlen stroemungsprofilen"
EP4172546B1 (fr) Procédé de fabrication d'un échangeur de chaleur à plaque à nervures et échangeur de chaleur à plaque à nervures
DE102014214038B4 (de) Gasturbine

Legal Events

Date Code Title Description
122 Ep: pct application non-entry in european phase

Ref document number: 12716195

Country of ref document: EP

Kind code of ref document: A2