WO2002038938A1 - Reacteur a turbine a gaz avec derivation et procede de refroidissement pour fluide caloporteur - Google Patents

Reacteur a turbine a gaz avec derivation et procede de refroidissement pour fluide caloporteur Download PDF

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Publication number
WO2002038938A1
WO2002038938A1 PCT/SK2000/000023 SK0000023W WO0238938A1 WO 2002038938 A1 WO2002038938 A1 WO 2002038938A1 SK 0000023 W SK0000023 W SK 0000023W WO 0238938 A1 WO0238938 A1 WO 0238938A1
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WO
WIPO (PCT)
Prior art keywords
heat
working medium
heat exchanger
gases
heat transferring
Prior art date
Application number
PCT/SK2000/000023
Other languages
English (en)
Inventor
Marek KOVÁC
Original Assignee
Kovac Marek
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 Kovac Marek filed Critical Kovac Marek
Priority to PCT/SK2000/000023 priority Critical patent/WO2002038938A1/fr
Priority to AU2001213231A priority patent/AU2001213231A1/en
Publication of WO2002038938A1 publication Critical patent/WO2002038938A1/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
    • F02C7/12—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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • 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 present invention relates to axial flow gas turbine engines and more particularly to a compressed air intercooler and heat exchanger for turbofan engines.
  • An axial flow turbomachine such as a gas turbine engine for an aircraft, has generally a compression section, a combustion section and a turbine section.
  • Working medium gases are drawn into the compression section, formed by rotor and stator blade rows, where they pass through several stages of compression causing the temperature and the pressure of the gases to rise.
  • a compressor discharges high pressure compressed air into a combustion chamber where it is mixed with fuel and the mixture burned. These hot pressurized gases are expanded through the turbine section to produce useful work and thrust.
  • the compression section commonly includes a fan section having a bypass duct.
  • Such engines are referred to as a bypass or a turbofan engines.
  • the bypass duct provides an annular flow path for secondary working medium gases which extend rearwardly about the primary flow path.
  • Primary working medium flow is also referred to as a core flow and corresponding appropriate parts of engine to as a core engine.
  • a fan rotor assembly in the fan section includes an array of fan blades which extend outwardly across the primary and secondary flow paths.
  • a plurality of fan exit guide vanes are disposed downstream of the fan blades in the fan duct to receive the relatively cool working medium gases of the secondary flow path.
  • a plurality of struts are typically disposed downstream of the fan exit guide vanes to support the stator structure and to transmit loads from the engine to its supporting structure.
  • the combustion gases In order to increase the efficiency and power of the turbine, it is desirable that the combustion gases have the highest possible temperature. On the other hand, it is desirable that the turbine components driven by the exhaust gases be maintained at a lower temperature than the combustion gases to prevent degradation of the components. It is known to use bypass air to cool compressed air in air to air heat exchanger located in the bypass duct.
  • U. S. Pat. No. 5,269,133 issued to Wallace, entitled “Heat exchanger for cooling a gas turbine” illustrates a heat exchanger located at the inlet of the combustor stage and comprises one or more stand pipe units extending radially from the engine and having a heat transfer member cooled externally by bypass air supplied by the fan.
  • a multistage axial flow compressor stator including a hollow stator blade which comprises an end portion of a heat pipe, and a hollow fin comprising the other end portion of the heat pipe, wherein, in use, said fin transfers heat from the blade to a coolant flowing over the fin.
  • the cooling means including a water cooled stator assembly located in a flow path of gas passing through the compressor when in operation.
  • a heat is transferred from the compressor of the primary working medium flow path to the secondary working medium flow path - bypass air, supplied by the fan in a bypass - turbofan engine, using coolant or cooling fluid or generally heat transferring medium (e.g. water, steam, oil) supplied to a first heat exchanger which is in flow communication with the primary working medium flow and then removed and cooled in a second heat exchanger which is in flow communication with the secondary working medium flow, further again removed back to the first heat exchanger forming closed circuit or closed-loop.
  • the cooling means may include a heat transferring medium cooled stator assembly located in a flow path of the primary working medium flow passing through the compressor.
  • the heating means may include a heat transferring medium heated stator assembly located in a flow path of the secondary working medium flow passing through the fan bypass portion of the gas turbine engine.
  • the closed-loop system may also include a heat transferring medium pump or pumps.
  • the heat transferring medium may be arranged in one or more independent closed- loops and some or all of them may include pressurized liquid heat transferring medium in order to increase its boiling point.
  • the system may also include one or more independent closed-loop supporting engine lubricating oil and engine accessories oil cooling system by putting cooled heat transferring medium in heat exchange relationship with the oil instead of primary working medium flow, using heat transferring medium to oil heat exchanger or direct oil cooling in the stator assembly located in the flow path of the secondary working medium flow passing through the fan bypass portion of the gas turbine engine.
  • a primary advantage of the present invention is the gain in engine efficiency which results from decreasing work required by the compressor as well as higher thrust of secondary working medium flow - bypass air at the same fan speed caused by heating of the secondary working medium flow, what means improvement of the Thrust Specific Fuel Consumption, and also improvement of the maximum thrust.
  • Another advantage is the effect on engine efficiency caused by increased ratio of the primary working medium flow temperature at the turbine inlet to the temperature of working medium flow discharged by the compressor at the same working medium flow temperature at the turbine inlet compared with the prior art engine.
  • Another advantage is the effect on engine efficiency or turbine blading durability alternatively caused by improved turbine blade cooling by cooler air.
  • FIG. 1 is a side elevation partially cross-sectional simplified schematic view of the bypass - turbofan engine.
  • FIG. 2 is a detailed view of a portion of the engine shown in FIG. 1 and illustrates a side elevation cross-sectional simplified schematic view of the compressor and fan parts of the bypass engine showing one embodiment of the present invention.
  • FIG. 3 is a cross sectional view taken along the line 3-3 of FIG. 4 and illustrates the heat exchanger located in the fan compartment of the engine.
  • FIG. 4 is a side elevation cross-sectional view of the heat exchanger located in the fan compartment of the engine.
  • FIG. 5 is a cross sectional view taken along the line 5-5 of FIG. 6 and illustrates the heat exchanger located in the primary working medium flow compressor of the engine.
  • FIG. 6 is a side elevation cross-sectional view of the heat exchanger located in the primary working medium flow compressor of the engine.
  • FIG. 7 is a front elevation view of the collector duct located around the stator assembly of the primary working medium flow path.
  • FIG. 8 is a front elevation view of the distribution duct located inside the annular space defined by the stator assembly of the secondary working medium flow path.
  • FIG. 1 is a side elevation partially cross-sectional simplified schematic view of the bypass - turbofan engine 10.
  • the engine has an axis of rotation Ar. Basically, this engine may be considered as comprising a fan section 12, a compressor section 14, a combustion section 16 and a turbine section 18.
  • a first portion of this relatively cool compressed air enters the fan bypass duct 26 defined, in part by core engine and a circumscribing fan cowl or nacelle 28, where is received by a plurality of fan exit guide vanes, as represented by the fan exit guide vane 42.
  • a plurality of struts as represented by the strut 44, are downstream of the fan exit guide vanes.
  • the struts extend radially between the inner wall and the outer wall and are circumferentially spaced for providing structural support to portions of the engine and to the nacelle.
  • Secondary working medium flow is then discharged through a fan nozzle 30. This annular flow path for secondary working medium gases is illustrated by the arrow 24.
  • the compressor section 14 includes rotor components such as rotor blades represented by the blade 32 and stator components such as inlet guide vanes represented by the inlet guide vane 34, a stator blades represented by the stator blade 36 and exit guide vanes represented by exit guide vane 38.
  • the rotor and stator assemblies have typically rotor and stator stages having rotor and stator blades which extend radially outwardly across the working medium flow path forming rotor and stator blade rows.
  • the compressor discharges working medium gases to a combustor 46 where they are mixed with fuel and the mixture burned. These hot pressurized gases are expanded through the turbine section 18 to produce useful work and thrust.
  • FIG. 2 is a detailed view of a portion of the engine shown in FIG. 1 and illustrates a side elevation cross-sectional simplified schematic view of the compressor and fan parts of the bypass engine.
  • the compressor H may consist of a low pressure compressor 50 and a high pressure compressor 52.
  • the compressor includes stator assembly such as hollow stator blades represented by the low pressure exit guide vane 54, the high pressure inlet " guide vane 56 and the stator blade 58.
  • Heat transferring medium preferably water or water- antifreeze mixture is circulated through the stator assembly of the compressor and further removed through the collector duct 66, the duct 68, the distribution duct 70 to the stator assembly of the secondary working medium flow path such as hollow fan exit guide vanes represented by the hollow fan exit guide vane 42 or hollow struts represented by the hollow strut 44 and further back through the collector duct, the duct and distribution duct to the stator assembly of the primary working medium flow path forming closed- loop as is shown by arrows.
  • the closed-loops include heat transferring medium pumps as represented by the pump 64 supporting circulation of heat transferring medium.
  • the hot working medium gases of the primary working medium flow are in flow communication with the stator assembly 54, 56, 58 and the stator assembly is in flow communication with the heat transferring medium. Heat from the hot pressurized gases in the compressor is transferred through the sidewalls of the stator assembly to the heat transferring medium which is thus heated. As is the heat transferring medium removed by circulation to the stator assembly of the secondary working medium flow path, heat from the relatively hot heat transferring medium is transferred through the sidewalls of stator assembly to the secondary working medium flow - bypass air which is thus heated.
  • the compressor may include one or more cooled stator assemblies, preferably stator assembly between low and high pressure compressor and all high pressure compressor stator assembly, which should be preferably arranged in independent closed- loops for every each compressor stage or stator blade row or generally part with the same temperature in order to avoid heat exchange effect between different stages of the compressor and thus heating of compressed air.
  • Bypass stator assembly may be arranged to more groups of blades for different closed-loops. Each group should be preferably created by axisymmetrically arranged blades.
  • liquid heat transferring medium system should be preferably created by pressurized closed-loops in order to improve boiling point of liquid heat transferring medium and every each closed-loop should preferably include heat transferring medium compensating tank with relief valve (not shown).
  • One or more closed-loops may be used to support oil cooling system in some engine operation conditions instead of cooling compressed gases, what expects to employ oil to heat transferring medium heat exchanger.
  • One or more closed-loops can be formed by part of secondary working medium flow path stator assembly in order to cool oil directly using engine or accessories oil instead of heat transferring medium.
  • FIG. 3 is a cross sectional view taken along the line 3-3 of FIG. 4 showing hollow airfoil shaped heat exchanger 44, located in the fan compartment of the engine, that is flown through by a heat transferring medium via channels represented by the channel 72.
  • the airfoil section includes a leading edge 74, a trailing edge 76, an inner sidewall 78 and outer sidewall 80.
  • FIG. 4 is a side elevation cross-sectional view of the heat exchanger 44 located in the fan compartment of the engine, that is flown through by a heat transferring medium via channels represented by the channel 82.
  • the airfoil shaped heat exchanger includes a leading edge 74 and a trailing edge 76.
  • Heat transferring medium is flowed into heat exchanger via inlet duct 88 and returned via exhaust duct 90. As heat transferring medium enters heat exchanger in distribution chamber 94 is distributed to plurality of channels and is collected again in collection chamber 96 before enters exhaust duct 90.
  • Arrow 92 illustrates circulation of the heat transferring medium in the heat exchanger.
  • FIG. 5 is a cross sectional view taken along the line 5-5 of FIG. 6 showing hollow airfoil shaped heat exchanger 58, located in the compressor of the core engine, that is flown through by a heat transferring medium via channels represented by channel 100.
  • the airfoil section includes a leading edge 102, a trailing edge 104, an inner sidewall 106 and outer sidewall 108.
  • FIG. 6 is a side elevation cross-sectional view of the heat exchanger 58 located in the compressor of the core engine, that is flown through by a heat transferring medium via channels represented by the channel 110.
  • the airfoil shaped heat exchanger includes a leading edge 102 and a trailing edge 104.
  • Heat transferring medium is flowed into heat exchanger via inlet duct J_16 and returned via exhaust duct 118. As heat transferring medium enters heat exchanger in distribution chamber 122 is distributed to plurality of channels and is collected again in collection chamber 124 before enters exhaust duct.
  • Arrow 120 illustrates circulation of the heat transferring medium in the heat exchanger.
  • FIG. 7 is a front elevation view of the collector duct 66 located around the stator assembly of the primary working medium flow path.
  • the collector duct represented by the collector duct 66 may be a toroid or a ring around the stator assembly of the primary working medium flow path or inside the annular space defined by the stator assembly of the secondary working medium flow path, for collecting heat transferring medium exhausts from the stator assembly components represented for example by the exhaust duct 118 which is connected to inlet 130 of the collector duct 66.
  • Exhaust duct 132 of the collector duct 66 is connected to duct 68 connecting collector duct 66 and distribution duct 70.
  • FIG. 8 is a front elevation view of the distribution duct 70 located inside the annular space defined by the stator assembly of secondary working medium flow path.
  • the distribution duct, represented by the distribution duct 70 may be a toroid or a ring around the stator assembly of the primary working medium flow path or inside the annular space defined by the stator assembly of the secondary working medium flow path, for distributing heat transferring medium to inlets of the stator assembly components represented for example by the inlet duct 88 which is connected to exhaust 140 of the distribution duct 70.
  • Inlet duct 142 of the distribution duct 70 is connected to duct 68.
  • stator blade row there may be more than one collector duct and the distribution duct for one stator blade row especially for the secondary working medium flow path stator assembly and thus may different blades of the same blade row be arranged to independent groups for different closed-loops.
  • working medium gases are flowed along the primary working medium flow path 22 and the secondary working medium flow path 24.
  • gases are flowed along the primary working medium flow path they pass through several stages of compression causing the temperature and the pressure of the gases to rise.
  • a compressor discharges high pressure compressed air into a combustion chamber where it is mixed with fuel and the mixture burned. These hot pressurized gases are expanded through the turbine section to produce useful work and thrust.
  • the gases flowed by the secondary working medium flow path are relatively cooler than those compressed in primary working medium flow path and mass flow of the gases of secondary working medium flow path is typically several times higher compare with the mass flow of the gases of the primary working medium flow path.
  • the gases of the secondary working medium flow path provide a good opportunity for cooling the gases of primary working medium flow path. Extraction and reintroduction of the main stream flow from and into the primary working medium flow path is associated with pressure losses and additional weight unacceptable in aircraft application.
  • turbofan engines During operation of a turbofan engine, heat is generated in various parts of the engine, its accessories and its associated fluid flow systems.
  • Prior art turbofan engines typically include fuel to oil heat exchanger and air to oil heat exchanger in order to keep oil in prescribed temperature limits, say maximum generator oil temperature 120 degrees Celsius and maximum lubricating oil temperature 160 degrees Celsius, although air to oil heat exchanger, typically using air from the secondary flow path, causes aerodynamic losses.
  • the temperature of the secondary working medium gases in the fan duct 26 may approach 55 degree Celsius and pressure 156 kPa.
  • Temperature of the primary working medium gases between low pressure compressor and high pressure compressor may approach 100 degree Celsius and corresponding pressure 220 kPa.
  • Temperature of the primary working medium gases discharged by the high pressure compressor may approach 470 degree Celsius and corresponding pressure 2,200 kPa.
  • Cooling stator assembly of the compressor of the primary working medium flow path by liquid heat transferring medium which is further removed and heats stator assembly of the secondary working medium flow path provides an effective method for cooling compressed gases of the primary working medium flow path and heating compressed gases of the secondary working medium flow path. Thus heat is transferred from the core compressor to bypass air.
  • the pressurized water based independent closed-loops serve twin purpose, one of which is ecological safety second is damage tolerance, the engine may operate, for example after heat transferring medium leaked out or pump failed, for approximately the same conditions as prior art engines. . .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un système de refroidissement (54, 56, 68) conçu pour un compresseur de noyau d'un réacteur à double flux. La chaleur produite par le compresseur de noyau (50, 52) est transférée dans un premier échangeur de chaleur (54, 56, 58) logé dans le circuit d'écoulement du compresseur de noyau vers le milieu de transfert de chaleur et ensuite évacuée vers un deuxième échangeur de chaleur (42, 44) logé dans une conduite de dérivation-circuit d'écoulement de milieu caloporteur secondaire et refroidi par l'air de dilution. Un système transfère la chaleur de l'air compressé dans le compresseur de noyau vers l'air de dilution et comprend de préférence une ou plusieurs boucles fermées de milieu de transfert de chaleur liquide pressurisé. Un système de refroidissement pour huile de réacteur utilisant de l'huile pour chauffer le milieu de transfert de chaleur de l'échangeur peut être monté dans un deuxième échangeur de chaleur.
PCT/SK2000/000023 2000-11-10 2000-11-10 Reacteur a turbine a gaz avec derivation et procede de refroidissement pour fluide caloporteur WO2002038938A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/SK2000/000023 WO2002038938A1 (fr) 2000-11-10 2000-11-10 Reacteur a turbine a gaz avec derivation et procede de refroidissement pour fluide caloporteur
AU2001213231A AU2001213231A1 (en) 2000-11-10 2000-11-10 Bypass gas turbine engine and cooling method for working fluid

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SK2000/000023 WO2002038938A1 (fr) 2000-11-10 2000-11-10 Reacteur a turbine a gaz avec derivation et procede de refroidissement pour fluide caloporteur

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WO2002038938A1 true WO2002038938A1 (fr) 2002-05-16

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DE102008024335A1 (de) * 2008-05-20 2009-11-26 Frank Schuster Gasturbinentriebwerk in Nebenstromausführung
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WO2014130103A2 (fr) 2013-02-20 2014-08-28 United Technologies Corporation Échangeurs de chaleur intégrés pour un réacteur à double flux à engrenages à faible rapport de pression de ventilateur
US8961114B2 (en) 2010-11-22 2015-02-24 General Electric Company Integrated variable geometry flow restrictor and heat exchanger
GB2517579A (en) * 2013-07-18 2015-02-25 Hamilton Sundstrand Corp Fluid cooling arrangement for a gas turbine engine and method
EP2990335A1 (fr) * 2014-08-26 2016-03-02 Rolls-Royce plc Système antigivre de moteur à turbine à gaz
US9617917B2 (en) 2013-07-31 2017-04-11 General Electric Company Flow control assembly and methods of assembling the same
EP3165719A1 (fr) * 2015-10-30 2017-05-10 General Electric Company Échangeur de chaleur de carter de turbomachine à gaz
EP3176409A1 (fr) * 2015-12-03 2017-06-07 General Electric Company Procédé de refroidissement en circuit fermé pour une turbomachine
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