WO2023237152A1 - Système d'entraînement pour aéronef - Google Patents

Système d'entraînement pour aéronef Download PDF

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Publication number
WO2023237152A1
WO2023237152A1 PCT/DE2023/100405 DE2023100405W WO2023237152A1 WO 2023237152 A1 WO2023237152 A1 WO 2023237152A1 DE 2023100405 W DE2023100405 W DE 2023100405W WO 2023237152 A1 WO2023237152 A1 WO 2023237152A1
Authority
WO
WIPO (PCT)
Prior art keywords
capacitor module
capacitor
bypass
drive system
channel
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.)
Ceased
Application number
PCT/DE2023/100405
Other languages
German (de)
English (en)
Inventor
Hermann Klingels
Sebastian Benke
Sascha Kaiser
Petra Kufner
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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
Priority claimed from DE102022115587.0A external-priority patent/DE102022115587A1/de
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of WO2023237152A1 publication Critical patent/WO2023237152A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
    • 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
    • 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
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/60—Application making use of surplus or waste energy

Definitions

  • an axial direction of a gas turbine runs parallel to an engine axis, that is to say a shaft axis of a drive shaft of the gas turbine.
  • a radial direction is perpendicular to the engine axis.
  • the gas turbine has a circumferential direction that describes a direction around the engine axis.
  • the main flow channel which can also be referred to as a core flow channel, is used to guide fluid through the gas turbine components, comprising a compressor, in particular a low-pressure and a high-pressure compressor, a combustion chamber and a turbine, in particular a high-pressure and a low-pressure turbine.
  • the exhaust gas from the main flow channel has a high temperature due to combustion in the combustion chamber.
  • the drive system is particularly preferably further developed in that the at least one capacitor module has a side surface that at least partially faces the air bypass flow direction.
  • the condenser module has an angle of attack relative to the air flow, which favors the flow through the condenser and can reduce pressure losses.
  • a first capacitor module and a second capacitor module are arranged in pairs as a pair of capacitor modules in the air bypass direction of the bypass channel, the first capacitor module having a first angle of attack relative to the flow direction in the bypass channel and the second capacitor module having a first angle of attack relative to the flow direction in the bypass channel has a second angle of attack that is different from the first angle of attack.
  • the first angle of attack and the second angle of attack have a different one Sign related to the direction of flow in the bypass channel.
  • the two angles of attack have the same absolute value.
  • the first capacitor module and the second capacitor module are connected to one another by an inlet panel arranged upstream, which divides an air bypass flow of the bypass flow duct and guides it along side surfaces of the first capacitor module and the second capacitor module facing the secondary air flow.
  • the inlet cover can advantageously contribute to generating or maintaining a favorable air flow and directing foreign objects away from the capacitor modules.
  • the first capacitor module and the second capacitor module are arranged in a V arrangement in the bypass channel. This advantageously creates nozzle-like areas for conducting the corresponding heated partial bypass flow between two capacitor modules, so that no additional partition walls have to be inserted into the bypass flow channel. In particular, at least one area with relatively undisturbed air flow in the bypass flow channel can be achieved between two pairs of capacitor modules.
  • exhaust channels of at least one, in particular two, capacitor modules open into a water separation device, in particular into an inlet channel of the water separation device.
  • exhaust ducts of three or more Capacitor modules flow into a water separation device. In particular, these can be neighboring capacitor modules. This allows the use of the installation space in the outer housing to be further improved.
  • the at least one capacitor module is delimited by an outlet panel arranged downstream.
  • the secondary air flow can be easily aligned in the desired direction of thrust with little loss.
  • a steam turbine is arranged concentrically to the main drive shaft and its mechanical power fed to the main drive shaft via a steam turbine gearbox.
  • the invention also relates to an aircraft with a drive system according to the invention.
  • Fig. 2 shows the exemplary embodiment of the drive system according to the invention in a circumferential view
  • FIGS. 1 and 2 An exemplary embodiment of a drive system according to the invention is described below with reference to FIGS. 1 and 2.
  • the drive system 1 is in a meridian section, that is, in one of the radial directions R and axial Direction Ax of the gas turbine spanned plane, shown.
  • the drive system is shown along the sections AA and BB shown laterally using a rolled-up representation of circumferential planes, that is, it is shown in a plane spanned by the axial direction Ax and circumferential direction U.
  • the fan 8 is coupled to the drive shaft 9 with a gear 11 also arranged in the inner housing 6.
  • the outer housing 5 surrounds the bypass channel 20 on the outside and delimits it at least in sections, while the inner housing 6 forms an inner channel wall for the bypass channel 20 and thus delimits it on the inside.
  • the exhaust gas from the main flow channel 10 is not ejected directly, but is after-treated in a water system 30 and a steam system 40.
  • the water system 30 and the steam system 40 are arranged in the gas turbine 2. Components of the water system 30 are arranged in the bypass channel 20 and partly in the inner housing 6 and the outer housing 5 of the gas turbine 2.
  • the water system 30 recovers water from the exhaust gas of the main stream and feeds the steam system 40 with water.
  • the steam system 40 evaporates the water and supplies hot steam to the main stream in order to increase its mass flow and thus the specific power of the gas turbine.
  • the flows of exhaust gas, water and steam are shown purely schematically in Fig. 1.
  • the main flow channel 10 has a compressor 12 in the direction of flow, a mixing chamber 48 downstream of the compressor 12 for mixing the compressed air and a hot steam, an adjoining combustion chamber 13, which supplies a fuel to the air-steam mixture and burns it into an exhaust gas, a high-pressure turbine 14 and a low-pressure turbine 15, which expand the exhaust gas and provide mechanical power for driving, and finally it into a turbine outlet housing 16.
  • the high-pressure turbine 14 drives a high-pressure compressor via a second shaft of the gas turbine 2.
  • a steam generator 41 of the steam system 40 is arranged downstream of the turbine outlet housing 16, through which the hot exhaust gas from the low-pressure turbine 15 flows outwards in the radial direction R.
  • the exhaust gas then flows further in the radial direction to the condenser 21 of the water system 30 and through this through exhaust gas channels 26, which also run in the radial direction.
  • the exhaust gas is further cooled in the condenser 21. During the cooling of the exhaust gas, water from the exhaust gas at least partially condenses, with the exhaust gas-water mixture continuing to flow radially outward into a water separation device 31.
  • the steam generator 41 is preferably designed as a so-called tube bundle heat exchanger in a cross-countercurrent arrangement to the exhaust gas with several passages. It is preferably accommodated rotationally symmetrically and concentrically to the engine axis within the inner housing of the gas turbine, that is, the core engine cowling.
  • the steam generator 41 includes a preheater 42 for heating the feed water, an evaporator 43 for converting the feed water into steam, and a superheater 44 for superheating the steam.
  • the arrangement within the steam generator is only shown schematically in FIG. Other configurations with more or fewer elements of the steam generator 41 are also possible.
  • the preheater 42, the evaporator 43 and the superheater 44 can be designed as pipes that cross one another in a spiral shape.
  • FIG. 2 sectional planes along the lines AA and BB are drawn into the gas turbine shown in the meridian section on the left side, the associated schematically illustrated circumferential planes of which are shown unrolled.
  • the first capacitor module 23 has a first angle of attack a, which corresponds in magnitude, that is to say an absolute value, to a second angle of attack a' of the second capacitor module 23', but has a different sign. This results in a V arrangement for the capacitor module pairs 25.
  • An internal distance i in the circumferential direction U is provided between the first capacitor module 23 and the second capacitor module 23 'of a capacitor module pair 25, which in the present exemplary embodiment is smaller everywhere along the axial extent of the capacitor is an external distance a in the circumferential direction U between two pairs of capacitor modules 25.
  • the air conveyed by the fan 8 is divided by the inlet panel 22 and then flows along the outer, i.e. along the air bypass direction facing side surfaces 24a of the capacitor modules 23, 23 '. Part of this air flows through cooling channels 24c between the plates of the capacitor modules 23, 23' onto the side surfaces 24b of the capacitor modules 23, 23' facing away from the air bypass flow direction.
  • Outlet covers 27, 27 'of a pair of capacitor modules 25 are blown out. In this way, the two adjacent outlet covers 27, 27' of a pair of capacitor modules 25 form a hot bypass nozzle 29.
  • the air flows through the capacitor modules exhaust heat is transferred to the air, causing its temperature to rise.
  • the exhaust gas cools until the water it contains is at least partially condensed and is in liquid form.
  • the exhaust gas is passed through exhaust channels 26 inside the condenser 21.
  • the exhaust channels 26 are located in each of the capacitor modules 23, 23 '.
  • the exhaust gas is guided radially outwards through the exhaust channels 26 into the inlet channels 32 of the water separation devices 31, which are arranged in the outer housing 5, which is also referred to as a cowling or nacelle.
  • the water separation devices 31 are connecting channels between the capacitor modules 23. 23 'and the core outlet nozzles 36.
  • the exhaust gas streams are combined from the two capacitor modules 23, 23 'of a pair of capacitor modules 24.
  • the exhaust gas After exiting the capacitor modules 23, 23 ', the exhaust gas first flows forward in an inlet channel 32 of the water separation device 31 in the direction of the engine inlet and then, after a 180 ° turn in a manifold 33 in the outlet channel 35 in the direction of the core engine nozzle 36.
  • a water separation device 31 in addition to the above-mentioned swirl generator 34, other elements that serve to separate water can be accommodated.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

L'invention concerne un système d'entraînement (1) pour un aéronef, comprenant une turbine à gaz (2), le système comportant un canal de flux principal (10) et un canal de flux secondaire (20), un système d'eau (30) et un système de vapeur (40), le système d'eau (30) comprenant au moins un dispositif de séparation d'eau (31) et un condenseur (21) doté d'au moins un module condenseur (23), la turbine à gaz (2) comprenant un carter (5, 6), en particulier un carter extérieur (5), qui délimite à l'extérieur le canal de flux secondaire (20), et/ou un carter intérieur (6) qui comprend le canal de flux principal (10). Un système d'entraînement dont le système d'eau et de vapeur est davantage intégré dans la turbine à gaz est réalisé en ce que le dispositif de séparation d'eau (31) est monté dans et/ou sur le carter extérieur (5), en particulier dans le capot, et/ou en ce que ledit au moins un module condenseur (23) est monté dans le canal de flux secondaire (20) et présente des canaux de gaz d'échappement (26) qui dirigent un gaz d'échappement du canal de flux principal (10) à travers le canal de flux secondaire (20) et dans et/ou à travers le carter extérieur (5).
PCT/DE2023/100405 2022-06-06 2023-05-31 Système d'entraînement pour aéronef Ceased WO2023237152A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE102022114213 2022-06-06
DE102022114213.2 2022-06-06
DE102022115587.0A DE102022115587A1 (de) 2022-06-06 2022-06-22 Antriebssystem für ein Luftfahrzeug
DE102022115587.0 2022-06-22

Publications (1)

Publication Number Publication Date
WO2023237152A1 true WO2023237152A1 (fr) 2023-12-14

Family

ID=87036168

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2023/100405 Ceased WO2023237152A1 (fr) 2022-06-06 2023-05-31 Système d'entraînement pour aéronef

Country Status (1)

Country Link
WO (1) WO2023237152A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4474624A3 (fr) * 2023-05-19 2025-02-26 RTX Corporation Séparateur d'eau pour moteur à turbine
US20250146440A1 (en) * 2023-11-07 2025-05-08 Rtx Corporation Strut microtube counterflow evaporator
US12366216B1 (en) 2024-10-09 2025-07-22 Rtx Corporation Thrust reverser in condenser exit duct

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5123242A (en) * 1990-07-30 1992-06-23 General Electric Company Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine
WO2020187345A1 (fr) 2019-03-15 2020-09-24 MTU Aero Engines AG Aéronef comprenant un moteur thermique et dispositif pour utiliser les gaz d'échappement du moteur thermique
DE102021201627A1 (de) * 2020-08-05 2022-02-10 MTU Aero Engines AG Wärmekraftmaschine mit Dampfzufuhrvorrichtung

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5123242A (en) * 1990-07-30 1992-06-23 General Electric Company Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine
WO2020187345A1 (fr) 2019-03-15 2020-09-24 MTU Aero Engines AG Aéronef comprenant un moteur thermique et dispositif pour utiliser les gaz d'échappement du moteur thermique
DE102021201627A1 (de) * 2020-08-05 2022-02-10 MTU Aero Engines AG Wärmekraftmaschine mit Dampfzufuhrvorrichtung
DE102021202602A1 (de) * 2020-08-05 2022-02-10 MTU Aero Engines AG Luftfahrzeug
WO2022028653A1 (fr) 2020-08-05 2022-02-10 MTU Aero Engines AG Aéronef

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4474624A3 (fr) * 2023-05-19 2025-02-26 RTX Corporation Séparateur d'eau pour moteur à turbine
US20250146440A1 (en) * 2023-11-07 2025-05-08 Rtx Corporation Strut microtube counterflow evaporator
US12331684B2 (en) * 2023-11-07 2025-06-17 Rtx Corporation Strut microtube counterflow evaporator
EP4553300A3 (fr) * 2023-11-07 2025-07-02 RTX Corporation Évaporateur à contre-courant de microtubes de entretoise
US12366216B1 (en) 2024-10-09 2025-07-22 Rtx Corporation Thrust reverser in condenser exit duct

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