WO2014033220A1 - Procédé de refroidissement permettant de faire fonctionner une turbine à gaz - Google Patents

Procédé de refroidissement permettant de faire fonctionner une turbine à gaz Download PDF

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Publication number
WO2014033220A1
WO2014033220A1 PCT/EP2013/067918 EP2013067918W WO2014033220A1 WO 2014033220 A1 WO2014033220 A1 WO 2014033220A1 EP 2013067918 W EP2013067918 W EP 2013067918W WO 2014033220 A1 WO2014033220 A1 WO 2014033220A1
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WO
WIPO (PCT)
Prior art keywords
air
gas turbine
pressure
combustion chamber
amount
Prior art date
Application number
PCT/EP2013/067918
Other languages
German (de)
English (en)
Inventor
Michael Wagner
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2014033220A1 publication Critical patent/WO2014033220A1/fr

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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
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • 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
    • F05D2260/212—Heat transfer, e.g. cooling by water injection
    • 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 method for operating a gas turbine with a combustion chamber and a secondary air system, in which air is taken off in at least two regions subjected to different pressures and located upstream of the combustion chamber and into a flow medium side downstream of the combustion chamber At least partially introduced.
  • a gas turbine is an internal combustion engine, consisting of the gas turbine in the strict sense with an upstream compressor and an intermediate combustion chamber.
  • the principle of operation is based on the Joule cycle: it compresses air via the blading of one or more compressor stages, then mixes them in the combustion chamber with a gaseous or liquid fuel, ignites and burns. The result is a hot gas (mixture of combustion gas and air), which relaxes in the subsequent turbine part, with thermal converts into mechanical energy and first drives the compressor.
  • the remaining portion is used in the shaft engine for driving a generator, a propeller, a rotor, a compressor or a pump.
  • the thermal energy accelerates the hot gas flow, which generates the thrust.
  • a stationary gas turbine basically consists of an inlet, a compressor, a combustion chamber, a turbine and an output shaft for shaft engines.
  • turbine is not used quite clearly, because strictly speaking, only one component of the gas turbine is actually a turbine, but on the other hand, the entire unit is colloquially referred to as a "gas turbine". Except for the inlet, all other moving components are coupled via one or more shafts.
  • Both the compressor and the turbine usually have several blades mounted on the shaft. Blades mounted in a plane each form a paddle wheel or impeller. The blades are slightly curved profiled, similar to an aircraft wing. Before each impeller is usually a stator.
  • stator and the impeller together are called stages. Usually, several such stages are connected in series. Since the stator is stationary, its vanes can be mounted both on the inside of the housing and on the outside of the housing, and thus provide a bearing for the shaft of the impeller.
  • a gas turbine For cooling the blading of the turbine, a gas turbine usually has a secondary air system. This removes at one or more points air in the compressor, which is guided past the combustion chamber and is introduced into the turbine, usually through corresponding cooling air openings.
  • the cooling air openings can also be arranged in the guide vanes, so that forms a protective air film here.
  • the turbine blade is for a nominal operating point respect. Lifespan, costs and cooling air consumption are optimized, which leads to a reduction in service life in unfavorable operating conditions such as overfiring. This becomes particularly important in part-load operation, in which to achieve increased machine flexibility in the future is increasingly over-fired. On the other hand, it is interested in a low base load combustion temperature to save cooling air, otherwise there is to be reckoned with an unnecessary overcooling of the components and thus a corresponding loss of efficiency. In addition, very unfavorable operating conditions, such as too low supply pressures in the case of unfavorable compressor prevent characteristic regardless of the combustion temperature.
  • the invention is therefore based on the object of specifying a method for operating a gas turbine and a secondary air system for a gas turbine, which allow particularly flexible modes of operation without limiting the life.
  • the invention is based on the consideration that an increased flexibility with respect to future requirements of the gas turbine mode of operation would be achievable if a free and continuous control of the amount, pressure and temperature of the cooling air would be possible.
  • the requirements are namely characterized by an increased operating range between low part load and peak load with very high turbine inlet temperatures.
  • the different operating ranges have very different requirements for cooling air pressure and cooling air temperature of the turbine blades, so that the fulfillment of all requirements is only very limited: generally cooling air is to be saved to maximize efficiency, ie low temperatures and pressures are desirable.
  • CO emissions are to be reduced, especially at partial load, which is possible due to high combustion temperatures.
  • these require a high cooling air consumption, ie high pressures with the lowest possible temperatures ren.
  • a sufficient supply pressure under unfavorable operating conditions such. B. partial load and low ambient temperatures.
  • the pressure and / or the amount of introduced air is increased when the combustion temperature is increased. This avoids excessive
  • the amount of coolant injected is increased, or the flow control valves are opened so as not to reduce the blade life. If at relatively high overfeed the supply pressure of the existing
  • Removal is not sufficient to ensure the life of the blade is advantageously switched to a higher extraction with sufficient supply pressure at moderate additional cooling air consumption. In the event of failure of the water system, sufficient pressure should be provided for the higher-level removal.
  • the method is switched at extreme partial load operation at low ambient temperatures of the gas turbine to a higher pressure level, ie increases the proportion of the removed in the area acted upon with the higher pressure air. Due to the physically given compressor characteristic, considerably lower removal pressures are to be expected in part-load operation. For this reason, the backflow margin, ie the difference in pressure between the cooling air pressure and the hot gas pressure at the point of introduction, should be switched over independently of the thermal load to the higher extraction, in particular when it is not reached. This has the advantage that in comparison to the usual procedure when selecting the compressor discharge point comparatively less security are kept, as can be switched to higher pressure. This reduces the required compressor capacity and thus increases the gas turbine performance for all operating points.
  • the supply pressure should be increased significantly under water injection in order not to reduce the life of the blade. Furthermore, the cooling air consumption is simultaneously increased at maximum water injection and maximum supply pressure, which considerably increases the potential for CO reduction.
  • the object is achieved by the secondary air system comprising at least two air extraction devices connected to different areas of the gas turbine, located on the output side and having a flow medium side associated with each of the air extraction devices is a flow control valve and wherein the secondary air system comprises an injection system for coolant, which is associated with a flow control valve.
  • a gas turbine advantageously comprises such a secondary air system and / or is advantageously operated with the described method.
  • a power plant includes such a gas turbine.
  • the advantages achieved by the invention are in particular that the combination of adeluftkaskadie- tion or switching to higher pressure level with controllable control valves and a Wassereindüsung for lowering the temperature in the supply line a flexible and infinitely adjustable combination of cooling air pressure and temperature can be achieved in order to optimize the operating conditions for all operating conditions. murti for lifetime and cooling air consumption.
  • this concept enables extreme operating conditions such as low partial load operation and overfiring to be intercepted.
  • FIG. 2 shows a schematic representation of a secondary air system with regulation of pressure, quantity and temperature of the cooling air
  • FIG. 3 shows a diagram of the temperature against the pressure of the cooling air in a secondary air system with an air extraction device without regulation
  • FIG. 5 shows a diagram of the temperature against the pressure of the cooling air in a secondary air system with an air extraction device with injection system
  • FIG. 6 shows a diagram of the temperature against the pressure of the cooling air in a secondary air system with an air extraction device with control and injection system
  • FIG. 7 shows a diagram of the temperature against the pressure of the cooling air in a secondary air system with two air sampling devices with control
  • FIG. 8 shows a diagram of the temperature against the pressure of the cooling air in a secondary air system with two air sampling devices with control and injection system
  • FIG. 9 shows the diagram from FIG. 8 with a representation of the directions of change in the case of specific control actions
  • FIG. 1 shows a gas turbine 100 in a longitudinal partial section of the upper half.
  • the gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner.
  • a rotation axis 102 axial direction
  • rotor 103 which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105
  • a toroidal combustion chamber 110 with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the combustion chamber 106 communicates with an annular hot gas channel 111.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed from two blade rings.
  • a blade row 125 formed from guide disk 120 follows.
  • the vanes 130 are attached to the stator 143, whereas the blades 120 of a row 125 are mounted on the rotor 103 by means of a turbine disk 133.
  • the rotor blades 120 thus form components of the rotor or rotor 103.
  • Coupled to the rotor 103 is a generator or a working machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is fed to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands on the rotor blades 120 in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine connected to it ,
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the highest thermal load in addition to the heat shield stones lining the combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • the guide vanes 130 are supplied with cooling air via a secondary air system 145.
  • the cooling air is guided there into the guide vanes 120 and emerges from the surface thereof in a plurality of cooling air openings in the manner of a film cooling in the hot gas channel 111.
  • the gas turbine 100 is part of a power plant, not shown. 2 shows schematically the components of the secondary air system 145. It has two air extraction devices 147, 149, of which the first air extraction device 147 is connected to a central region of the compressor 105, the second air extraction device 149 connected to an end portion of the compressor 105. In the end region, there is a higher pressure than in the middle region.
  • the air sampling device 147 is a line 151 downstream of a flow control valve 153.
  • the air extraction device 149 is a line 155 connected downstream of a flow control valve 157.
  • the lines 151, 155 open into a common line 159, which leads to an air introduction device 161, the cooling air in the turbine 108, in particular in the guide vanes 130th
  • an injection system 163 is provided for water, which also includes a not shown in detail flow control valve.
  • the secondary air system 145 may also include a plurality of parallel arrangements according to FIG. 2, which lead into different areas of the turbine 108 and remove air in different areas of the compressor 105.
  • FIGS. 3 to 9 each show a diagram of the cooling air temperature plotted against the cooling air pressure, the illustrations being only schematic, and therefore no numerical values are shown on the axes.
  • a schematic representation of the associated configuration of the secondary air system 145 is arranged in the right-hand edge of the diagram.
  • FIG. 3 shows an uncontrolled cooling air line 151 from the air extraction device 147 in the compressor 105 to the air introduction device 161 in the turbine 108.
  • the pressure and temperature of the air can not be influenced and are determined by the conditions in the compressor 105, shown as point 165.
  • FIG. 4 shows a regulated cooling air line 151 with a flow control valve 153 from the air extraction device 147 in the compressor 105 to the air introduction device 161 in the turbine 108.
  • the temperature of the air can not be influenced and is determined by the conditions in the compressor 105
  • Flow control valve 153 vary, shown as line 167. The maximum is represented by the point 165.
  • FIG. 5 shows an uncontrolled cooling air line 151 with an injection system 163 for water from the air extraction device 147 in the compressor 105 to the air introduction device 161 in the turbine 108.
  • the pressure of the air can not be influenced and is determined by the conditions in the compressor 105. However, the temperature can be due to injection system 163, shown as line 167. The maximum is represented by point 165.
  • FIG. 6 shows a regulated cooling air line 151 with a flow control valve 153 and an injection system 163 for water from the air extraction device 147 in the compressor 105 to the air introduction device 161 in the turbine 108.
  • Pressure and temperature of the cooling air can be compared to the conditions in the compressor 105 by appropriate control of the flow control valve 153 and injection system 163, shown as area 169.
  • the uncontrolled operating point is represented by point 165.
  • FIG. 7 shows a first regulated cooling air line 151 with a flow control valve 153 and a second regulated one
  • Cooling air line 155 with a flow control valve 157 which open into a common line 159.
  • the first cooling air line 151 is connected on the input side to the air extraction device 147 in the compressor 105, the second cooling air line 155 to the air extraction device 149 in a region of the compressor 105 subjected to higher pressure.
  • the common line 159 leads to the air introduction device 161 in the turbine 108.
  • the pressure can thus be varied in each case, represented by the lines 167 and 171, respectively.
  • the uncontrolled operating point is represented by the points 165 and 173, respectively. Due to the physical conditions in the compressor 105, the temperature level of the air from the air extraction device 147 is lower than that from the air extraction device 149.
  • FIGS. 8 and 9 show corresponding diagrams of the configuration from FIG. 2, which is not additionally shown here.
  • the combination of the injection system 163 with the configuration of FIG. 7 in FIG. 8 results in infinite controllability of pressure and temperature, represented by the area 175 with the maximum represented by the point 173 and the partially underlying area 169.
  • FIG. 9 shows all the features of FIG. 8, wherein here also the point 165, which represents the maximum with respect to the surface 169, is also shown. From the point 165, which roughly represents the operating state in a simple, uncontrolled system of FIG. 3, the operating state can now be optimally optimized with regard to pressure and temperature, depending on the desired driving style, represented by arrows 177, 179, 181, 183 : Arrows 177 show an increase in the pressure z. For example, at partial load with adaptation of the temperature to expand the CO emissions-compliant operating range of the gas turbine 100. Arrow 179 shows the maximum of cooling air consumption by maximum reduction of the temperature at maximum
  • FIGS. 10 and 11 show the cooling air temperature plotted against the relative supply pressure (pressure of the cooling air divided by pressure of the hot gas) of the respective guide blade 130 in the compressor 105, in each case for the configuration from FIG. 2. Depicted is the mass flow of the cooling air corresponding to the respective point represented in legend 184.
  • FIG. 10 describes the control concept on a real gas turbine 100 during base-load operation: Box 185 describes the possible operating range of a pressure-controlled compressor removal with water injection, and box 187 describes the pressure-controlled, higher-level compressor removal or the compressor end space with water injection.
  • the lower limit of the supply pressure is always the back flow margin, represented by line 189, which must not be exceeded, irrespective of the operating regime. This is particularly important in film-cooled blades of importance.
  • the design of the blade is carried out under nominal conditions with optimization of costs, service life and cooling air consumption.
  • the associated operating point is represented by point 191. Starting from this point 191, it is possible to vary supply pressure and temperature (curve 193) so that the blade temperature and temperature gradient are identical under nominal conditions and thus no limitation for the service life is to be expected. If the injection system 163 fails, the thermal load on the blade can be kept identical by opening the flow control valve 153, but at the expense of additional cooling air consumption, see point 195. Switchover to the higher removal, ie. H. the air extraction device 149 is not yet required.
  • the system allows a switchover to the higher extraction, see point 199, with water injection and sufficient supply pressure with moderate additional cooling air consumption. If the injection system 163 fails, sufficient pressure must be available for the higher extraction, see item 203. In the case of under-firing, the supply pressure can be reduced so that a cooling-air saving can be achieved to increase the efficiency, see point 205. The technical limits of the blade ( BFM line 189). If the injection system 163 fails, the cooling air pressure can also be increased here, see point 205.
  • FIG. 11 shows the diagram analogous to FIG. 10 for the case of a low partial load. Due to the physically given compressor characteristics, considerably lower removal pressures are to be expected, characterized by a displacement of the boxes 185 and 187 to smaller supply pressures. If the BFM line 189 is not reached, the system switches over to the higher extraction, regardless of the thermal load, see item 209.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé permettant de faire fonctionner une turbine à gaz (100) comprenant une chambre de combustion (106) et un système d'air secondaire (145). Selon ledit procédé, de l'air est prélevé dans au moins deux zones soumises à des pressions différentes et se trouvant en amont de la chambre de combustion (106) côté écoulement du fluide, et est au moins en partie introduit dans une zone se trouvant en aval de la chambre de combustion (106) côté écoulement du fluide. L'invention vise à assurer un fonctionnement particulièrement flexible sans réduction de la durée de vie. A cet effet, le procédé consiste à réguler la quantité, la pression et la température de l'air introduit en commandant la quantité d'air prélevée dans chaque zone de prélèvement et en injectant un fluide de refroidissement dans l'air prélevé au moyen d'un système d'injection (163), et en commandant la quantité de fluide de refroidissement injecté.
PCT/EP2013/067918 2012-08-31 2013-08-29 Procédé de refroidissement permettant de faire fonctionner une turbine à gaz WO2014033220A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012215478 2012-08-31
DE102012215478.7 2012-08-31

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3070300A1 (fr) * 2015-03-19 2016-09-21 General Electric Company Système de génération de puissance possédant un compresseur créant un écoulement d'air en excès et son d'injection de fluide de refroidissement
US9822670B2 (en) 2015-03-19 2017-11-21 General Electric Company Power generation system having compressor creating excess air flow and turbo-expander for cooling inlet air
US9828887B2 (en) 2015-03-19 2017-11-28 General Electric Company Power generation system having compressor creating excess air flow and turbo-expander to increase turbine exhaust gas mass flow
EP3348810A1 (fr) * 2017-01-17 2018-07-18 United Technologies Corporation Système d'air de refroidissement refroidi par injection pour moteur à turbine à gaz et procédé correspondant
US11274611B2 (en) 2019-05-31 2022-03-15 Pratt & Whitney Canada Corp. Control logic for gas turbine engine fuel economy
US11274599B2 (en) 2019-03-27 2022-03-15 Pratt & Whitney Canada Corp. Air system switching system to allow aero-engines to operate in standby mode
US11326525B2 (en) 2019-10-11 2022-05-10 Pratt & Whitney Canada Corp. Aircraft bleed air systems and methods
US11391219B2 (en) 2019-04-18 2022-07-19 Pratt & Whitney Canada Corp. Health monitor for air switching system
US11859563B2 (en) 2019-05-31 2024-01-02 Pratt & Whitney Canada Corp. Air system of multi-engine aircraft

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JPH0754669A (ja) * 1993-08-09 1995-02-28 Mitsubishi Heavy Ind Ltd ガスタービン冷却空気制御装置
EP0995891A2 (fr) * 1998-10-20 2000-04-26 Asea Brown Boveri AG Turbomachine et sa méthode d'opération
US20100154434A1 (en) * 2008-08-06 2010-06-24 Mitsubishi Heavy Industries, Ltd. Gas Turbine
DE102012011294A1 (de) * 2011-06-16 2012-12-20 Alstom Technology Ltd. Verfahren zum Kühlen einer Gasturbinenanlage sowie Gasturbinenanlage zur Durchführung des Verfahrens

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0754669A (ja) * 1993-08-09 1995-02-28 Mitsubishi Heavy Ind Ltd ガスタービン冷却空気制御装置
EP0995891A2 (fr) * 1998-10-20 2000-04-26 Asea Brown Boveri AG Turbomachine et sa méthode d'opération
US20100154434A1 (en) * 2008-08-06 2010-06-24 Mitsubishi Heavy Industries, Ltd. Gas Turbine
DE102012011294A1 (de) * 2011-06-16 2012-12-20 Alstom Technology Ltd. Verfahren zum Kühlen einer Gasturbinenanlage sowie Gasturbinenanlage zur Durchführung des Verfahrens

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3070300A1 (fr) * 2015-03-19 2016-09-21 General Electric Company Système de génération de puissance possédant un compresseur créant un écoulement d'air en excès et son d'injection de fluide de refroidissement
US9822670B2 (en) 2015-03-19 2017-11-21 General Electric Company Power generation system having compressor creating excess air flow and turbo-expander for cooling inlet air
US9828887B2 (en) 2015-03-19 2017-11-28 General Electric Company Power generation system having compressor creating excess air flow and turbo-expander to increase turbine exhaust gas mass flow
US9863284B2 (en) 2015-03-19 2018-01-09 General Electric Company Power generation system having compressor creating excess air flow and cooling fluid injection therefor
EP3348810A1 (fr) * 2017-01-17 2018-07-18 United Technologies Corporation Système d'air de refroidissement refroidi par injection pour moteur à turbine à gaz et procédé correspondant
US10961911B2 (en) 2017-01-17 2021-03-30 Raytheon Technologies Corporation Injection cooled cooling air system for a gas turbine engine
US11732643B2 (en) 2019-03-27 2023-08-22 Pratt & Whitney Canada Corp Air system switching system to allow aero-engines to operate in standby mode
US11274599B2 (en) 2019-03-27 2022-03-15 Pratt & Whitney Canada Corp. Air system switching system to allow aero-engines to operate in standby mode
US11391219B2 (en) 2019-04-18 2022-07-19 Pratt & Whitney Canada Corp. Health monitor for air switching system
US11725595B2 (en) 2019-05-31 2023-08-15 Pratt & Whitney Canada Corp. Control logic for gas turbine engine fuel economy
US11274611B2 (en) 2019-05-31 2022-03-15 Pratt & Whitney Canada Corp. Control logic for gas turbine engine fuel economy
US11859563B2 (en) 2019-05-31 2024-01-02 Pratt & Whitney Canada Corp. Air system of multi-engine aircraft
US11326525B2 (en) 2019-10-11 2022-05-10 Pratt & Whitney Canada Corp. Aircraft bleed air systems and methods

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