(19)
(11)EP 2 904 251 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
26.06.2019 Bulletin 2019/26

(21)Application number: 13843574.8

(22)Date of filing:  15.03.2013
(51)International Patent Classification (IPC): 
G06Q 10/06(2012.01)
F02C 9/00(2006.01)
(86)International application number:
PCT/US2013/032047
(87)International publication number:
WO 2014/055124 (10.04.2014 Gazette  2014/15)

(54)

METHOD OF DEFINING GAS TURBINE ENGINE CONTROL RATINGS

VERFAHREN ZUR FESTLEGUNG VON GASTURBINENSTEUERUNGSNENNWERTEN

PROCÉDÉ DE DÉFINITION DE CALIBRES DE RÉGLAGE D'UN MOTEUR À TURBINES À GAZ


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 01.10.2012 US 201261708353 P

(43)Date of publication of application:
12.08.2015 Bulletin 2015/33

(73)Proprietor: United Technologies Corporation
Farmington, CT 06032 (US)

(72)Inventor:
  • POTH, JR., Stefan M.
    South Windsor, Connecticut 06074 (US)

(74)Representative: Dehns 
St. Brides House 10 Salisbury Square
London EC4Y 8JD
London EC4Y 8JD (GB)


(56)References cited: : 
EP-A2- 1 811 133
WO-A1-00/71876
US-A1- 2012 124 965
EP-A2- 2 289 799
US-A- 5 893 040
US-B2- 6 748 744
  
      
    Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


    Description

    CROSS REFERENCE TO RELATED APPLICATION



    [0001] This application claims priority to United States Provisional Application No. 61/708,353 filed on October 1, 2012.

    BACKGROUND



    [0002] A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section.

    [0003] Operation of the gas turbine engine is controlled according to schedule of thrust settings. Engine operating parameters are modified and adjusted to provide the desired thrust setting according to the schedule. Different thrust settings are defined according to the schedule for different aircraft operating periods, such as for takeoff, climb, cruise and landing. Each operational period includes a different schedule of engine thrust, also referred to as a rating. Within each operating period adjustments are made to account for variations in temperature, pressure, altitude, aircraft weight and many other variable factors.

    [0004] Moreover, each airframe manufacturer defines the desired thrust or rating schedule for each operating condition. Further, each airframe manufacturer may also require different rating schedules for different parts of the operating sequence from take-off to landing. The rating schedules are defined as part of an engine control program and are typically uniquely constructed for each engine and/or aircraft platform. Development of control programs can be costly and time intensive and therefore it is desirable to design a system that could be utilized for many different engine and aircraft platforms.

    [0005] US 2012/124965A1 relates to a variable area fan nozzle fan flutter management system.

    SUMMARY



    [0006] A method of defining a rating schedule for a gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes defining a plurality of generic rating structures adapted to receive corresponding groups of rating information, determining a set of desired ratings for a selected gas turbine engine, mapping each of the set the desired ratings to a corresponding one of the plurality of generic rating structures, generating a unique rating structure including the desired ratings mapped to the generic rating structure, and loading the generated unique rating structure into a controller that is configured to control the selected gas turbine engine according to the unique rating structure.

    [0007] In a further embodiment of the foregoing method, the desired ratings include engine thrust levels for specific operational conditions.

    [0008] In a further embodiment of any of the foregoing methods, includes defining a derate schedule for at least one of the generated unique rating structure and loading the derate schedule into the controller to correspond with the corresponding unique rating structure.

    [0009] In a further embodiment of any of the foregoing methods, at least one of the ratings includes auxiliary power (APR) rating.

    [0010] In a further embodiment of any of the foregoing methods, at least one of the desired ratings includes a take-off (MTO) power rating.

    [0011] In a further embodiment of any of the foregoing methods, at least one of the desired ratings includes a continuous (MCT) power rating.

    [0012] In a further embodiment of any of the foregoing methods, at least one of the desired ratings includes a climb power (MCL) rating.

    [0013] In a further embodiment of any of the foregoing methods, at least one of the desired ratings includes a cruse power (MCR) rating.

    [0014] In a further embodiment of any of the foregoing methods, includes a derate value for adjusting the desired rating.

    [0015] In a further embodiment of any of the foregoing methods, includes a pointer for designating an auxiliary power rating for a desired power rating.

    [0016] A system for operating a gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a plurality of generic rating structures adapted to receive corresponding groups of rating information, an input for receiving rating information for a selected gas turbine engine and for assigning the received rating information to one of the plurality of generic rating structures, and a controller for accessing the groups of rating information and for producing an output communicating for controlling the gas turbine engine to produce thrust corresponding to the rating information.

    [0017] In a further embodiment of the foregoing system, the generic rating structures define logic structures for accepting rating values corresponding to the selected gas turbine engine.

    [0018] In a further embodiment of any of the foregoing systems, the plurality of generic rating structures includes a corresponding plurality of generic derate structures for accepting information relating to adjusting the rating information responsive to selected operating conditions.

    [0019] In a further embodiment of any of the foregoing systems, the received rating information includes a takeoff rating.

    [0020] In a further embodiment of any of the foregoing systems, the received rating information includes a bump rating.

    [0021] In a further embodiment of any of the foregoing systems, the received rating information includes a continuous rating.

    [0022] In a further embodiment of any of the foregoing systems, the received rating information includes an auxiliary power rating.

    [0023] In a further embodiment of any of the foregoing systems, includes a throttle input representing a desired thrust communicating with the controller such that the controller modifies the output for controlling the gas turbine engine responsive to the throttle input.

    [0024] Although the different examples have the specific components shown in the illustrations, embodiments of this disclosure are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another one of the examples.

    [0025] These and other features disclosed herein can be best understood from the following specification and drawings, the following of which is a brief description.

    BRIEF DESCRIPTION OF THE DRAWINGS



    [0026] 

    Figure 1 is a schematic view of an example gas turbine engine.

    Figure 2 is a schematic view of an example method of mapping ratings to a generic logic structure.

    Figure 3 is a table illustrating different mapped ratings to a common generic logic structure.

    Figure 4 is a table illustrating one example rating schedule mapped to the generic logic structure.

    Figure 5 is another table illustrating another example rating schedule mapped to the generic logic structure.

    Figure 6 is another table illustrating another example rating schedule mapped to the generic logic structure.


    DETAILED DESCRIPTION



    [0027] Figure 1 schematically illustrates an example gas turbine engine 20 that includes a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. Alternative engines might include an augmenter section (not shown) among other systems or features. The fan section 22 drives air along a bypass flow path B while the compressor section 24 draws air in along a core flow path C where air is compressed and communicated to a combustor section 26. In the combustor section 26, air is mixed with fuel and ignited to generate a high pressure exhaust gas stream that expands through the turbine section 28 where energy is extracted and utilized to drive the fan section 22 and the compressor section 24. In this example the turbine section 28 drives a geared architecture 30 that in turn drives the fan section 22. The geared architecture 30 enables the turbine section 28 and the fan section 22 to each rotate at closer to optimal speeds.

    [0028] Although the disclosed non-limiting embodiment depicts a turbofan gas turbine engine, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines; for example a turbine engine including a three-spool architecture in which three spools concentrically rotate about a common axis and where a low spool enables a low pressure turbine to drive a fan via a gearbox, an intermediate spool that enables an intermediate pressure turbine to drive a first compressor of the compressor section, and a high spool that enables a high pressure turbine to drive a high pressure compressor of the compressor section. Moreover other power turbine machines such as a turboshaft engine utilized in rotary wing aircraft and power generation applications.

    [0029] An engine control system 18 includes an engine controller 32 that provides an output 34 to control the gas turbine engine 20 to obtain the desired level of thrust output. The controller 32 is in communication with a throttle 36 and a rating schedule 40. The throttle 36 provides a throttle position output 38 to the controller 32 and the rating schedule 40 includes different thrust ratings that are selected for different aircraft operating conditions.

    [0030] Engine control is accomplished by monitoring engine operational characteristics with sensors 46 that provide an output to the controller 32. As appreciated, a plurality of different sensors throughout the engine are utilized and schematically represented by the sensor 46. The sensor 46 provides information indicative of an engine thrust production or output.

    [0031] Each engine will include several different engine thrust levels that correspond to different part of aircraft operation such as take-off, cruise or landing. Thrust ratings are certified for each engine an airframe combination. The rating schedule is utilized to maintain a balance between providing sufficient thrust to enable operation within predetermined parameters while limiting thrust to reduce wear on the engine. Thrust production is also referred to as an engine rating and different aircraft manufacturers utilize different rating values, terms and control schemes. For example, one airframe may have a takeoff (MTO) rating, a bump rating, a continuous (MCT) rating and a climb (MCL) rating while another may replace the bump rating with an auxiliary power reserve (APR) rating. In this example, the rating schedule includes ratings 42A-D. Moreover, one airframe may have a takeoff (MTO) rating, a bump rating, a continuous (MCT) rating and a climb (MCL) rating while another may replace the bump rating with an auxiliary power reserve (APR) rating.

    [0032] Additionally, each category of rating may further have different variations. For example, engine idle ratings may include different variants for ground, flight and approach conditions. Moreover, a cruise (MCR) rating may have been included to instruct engine operating parameters during cruise operations. The cruise (MCR) rating may also have variants to address different aircraft operating conditions.

    [0033] The ratings 42A-D is typically determined for a standard set of environmental conditions such as temperature and pressure. Accordingly, some adjustment is provided to enable variation from the ratings 42A-D based on environmental parameters along with aircraft payload and other aircraft variable characteristics. The specific derate is selected by the pilot to balance aircraft performance with engine durability. The pilot selects the desired derate based on the environment and aircraft configuration to minimize operating stresses on the engine. The adjustments are referred to by those skilled in the art as derate and are associated with each of the ratings 42A-D. In this example each rating includes derates 44A-D. As appreciated, although two derates 44A-D are shown that correspond with each rating 42A-D, any number of derates could be associated with each rating 42A-D.

    [0034] Because each aircraft manufacturer utilizes different ratings, engines controls and rating schedules are different. Therefore one rating schedule and control logic cannot accommodate all potential combinations. Simply constructing a common logic structure with ratings for all aircraft manufactures is inefficient and memory intensive.

    [0035] Referring to Figure 2 with continued reference to Figure 1, a disclosed method provides a generic rating structure 50 that reuses a common memory and algorithm in a way that can be customized for individual airframer rating requirements. In this example the generic rating structure 50 is a memory device that includes structured memory locations referred to as tables 52A-C and corresponding memory locations for derate values 54A-C.

    [0036] Accordingly, the example system 18 provides a generic logic set 50 that can be mapped to the desired rating. For example, instead of having APR, MTO, MCT and MCL ratings, generic rating structures 52A-D are available. An input device 56 receives rating information schematically indicated at 58A-C and assigns portions of the generic logic structure 50 to receive the input rating information 58A-C.

    [0037] Therefore, for a given airframe customer, the generic logic structures 52A-C are mapped to the desired and selected rating structures 58A-C that include some combination of APR, MTO, MCT, MCR and MCL. A final rating schedule is constructed for each different airframe from the same generic rating structure 50 that is mapped to the different set of ratings 58A-C. Accordingly, final rating schedules 60A-C are generated to include the desired combination of APR, BUMP, MTO, MCT and MCL.

    [0038] The final rating schedules 60A may not include all possible ratings, one customer may utilize APR and MTO, while yet another customer may utilize only MTO, MCT and MCL. Moreover, some ratings may require the use of different maximum thrust rating values referred to as Namplates as is shown by way of example in the rating schedule 60A. Moreover, in some completed rating schedules, some logic locations would be unused such as is indicated at 60B.

    [0039] Referring to Figure 3, the tables 52A-C of the generic logic structure is shown mapped to provide rating schedules 60A-C according to different airframe requirements. The generic tables 52A-C along with the derate A-C are present in each of the different rating schedules 60A-C, but hold different rating values and conditions that correspond with the airframe rating requirements.

    [0040] Referring to Figures 4, 5 and 6, along with the different rating structures that are generated from the common logic structure different auxiliary power rating pointers 62A-C are applied to define transition between ratings. As is schematically shown in Figure 4, the auxiliary power rating is a term known in the art utilized to describe a reserve amount of thrust accommodated at each power rating. Like the thrust ratings, the APR rating changes for each rating and derate value. The example generic logic structure 50 enables adaptation to different fixed rate transitions as indicated at 64A. In the example show in Figure 4, there are many defined fixed derate transitions 64A defined for the rating schedule 60A. Additionally, a nameplate selector 66A is enabled for selecting which of the ratings will provide the maximum engine thrust. In most rating schedules only a single nameplate is selected, however the disclosed generic logic structure 50 enables adaptations to include several nameplate selection as is indicated in Figure 4.

    [0041] Referring to Figures 5 and 6, different rating schedule are illustrated in comparison to the original data structure 50. The rating schedules 60B and 60C do not utilize all of the tables 52A-C in the generic structure 50 as not all of the space is required to accommodate the different requirements. Moreover, the placement of each rating value can be within any of the tables 52A-C and is not constrained with beginning with the first available table such as for example 52A. Moreover the APR pointers 62B and 62C may not all be utilized. In the rating schedules 60B and 60C, only a single Namplate selector 66B and 66C are utilized and shown.

    [0042] It should be understood that three tables 52A-C and three derates 54A-C for each of the tables 52A-C are shown by way of example, but any number of tables, and derates are within the contemplation of this disclosure to provide the generic logic structure capable of receiving information for any number of combination of rating settings and requirements.

    [0043] Moreover, the example method is performed on the system 18 or another computing device such as microprocessor or the disclosed controller 32. In terms of hardware architecture, the controller can include a processor, a memory, and one or more input and/or output (I/O) device interface(s) that are communicatively coupled via a local interface. The local interface can include, for example but not limited to, one or more buses and/or other wired or wireless connections. The local interface may have additional elements, which are omitted for simplicity, such as controllers, buffers (caches), drivers, repeaters, and receivers to enable communications. Further, the local interface may include address, control, and/or data connections to enable appropriate communications among the aforementioned components.

    [0044] The processor may be a hardware device for executing software, particularly software stored in memory. The processor can be a custom made or commercially available processor, a central processing unit (CPU), an auxiliary processor among several processors associated with the computing device, a semiconductor based microprocessor (in the form of a microchip or chip set) or generally any device for executing software instructions.

    [0045] Moreover, the completed rating schedule 40, can be stored in a memory and that the memory can include any one or combination of volatile memory elements (e.g., random access memory (RAM, such as DRAM, SRAM, SDRAM, VRAM, etc.)) and/or nonvolatile memory elements (e.g., ROM, hard drive, tape, CD-ROM, etc.). Moreover, the memory may incorporate electronic, magnetic, optical, and/or other types of storage media. Note that the memory can also have a distributed architecture, where various components are situated remotely from one another, but can be accessed by the processor.

    [0046] The software in the memory may include one or more separate programs, each of which includes an ordered listing of executable instructions for implementing logical functions. A system component embodied as software may also be construed as a source program, executable program (object code), script, or any other entity comprising a set of instructions to be performed. When constructed as a source program, the program is translated via a compiler, assembler, interpreter, or the like, which may or may not be included within the memory.

    [0047] The Input/Output devices that may be coupled to system I/O Interface(s) may include input devices, for example but not limited to, a keyboard, mouse, scanner, microphone, camera, proximity device, etc. Further, the Input/Output devices may also include output devices, for example but not limited to, a printer, display, etc. Finally, the Input/Output devices may further include devices that communicate both as inputs and outputs, for instance but not limited to, a modulator/demodulator (modem; for accessing another device, system, or network), a radio frequency (RF) or other transceiver, a telephonic interface, a bridge, a router, etc.

    [0048] When the controller 32 is in operation, the processor can be configured to execute software stored within the memory, to communicate data to and from the memory, and to generally control operations pursuant to the software and to the rating schedule 40. Software in memory, in whole or in part, is read by the processor, perhaps buffered within the processor, and then executed.

    [0049] The system 18 and controller 32 utilizes the generated rating schedule 40 to control operation of the engine 20 and provide the desired thrust and performance while mitigating unnecessary wear extend engine operational life.

    [0050] The disclosed system and method provides a generic framework for ratings combined with simple selection logic to customize rating schedules for multiple airframe customers. This reduces software design effort, reduces memory consumption, and reduces processor throughput.

    [0051] Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this disclosure. For that reason, the following claims should be studied to determine the scope and content of this disclosure.


    Claims

    1. A method of defining a rating schedule for an aircraft gas turbine engine characterised by:

    defining a plurality of generic aircraft operation rating structures (52 A-D) adapted to receive corresponding groups of rating information (58 A-C);

    determining a set of desired aircraft operation ratings (42 A-D) for a selected gas turbine engine, wherein the desired aircraft operation ratings include engine thrust levels for specific aircraft operational conditions;

    mapping each of the set the desired aircraft operation ratings to a corresponding one of the plurality of generic aircraft operation rating structures;

    generating a unique aircraft operation rating structure including the desired ratings mapped to the generic aircraft operation rating structures; and

    loading the generated unique aircraft operation rating structure into a controller that is configured to control the selected gas turbine engine according to the unique aircraft rating structure.


     
    2. The method as recited in claim 1, including defining a derate schedule for at least one of the generated unique rating structure and loading the derate schedule into the controller to correspond with the corresponding unique rating structure.
     
    3. The method as recited in any preceding claim, wherein at least one of the ratings comprises auxiliary power (APR) rating.
     
    4. The method as recited in any preceding claim, wherein at least one of the desired ratings comprises a take-off (MTO) power rating.
     
    5. The method as recited in any preceding claim, wherein at least one of the desired ratings comprises a continuous (MCT) power rating.
     
    6. The method as recited in any preceding claim, wherein at least one of the desired ratings comprises a climb power (MCL) rating.
     
    7. The method as recited in any preceding claim, wherein at least one of the desired ratings comprises a cruse power (MCR) rating.
     
    8. The method as recited in any preceding claim, including a derate value for adjusting the desired rating.
     
    9. The method as recited in any preceding claim, including a pointer for designating an auxiliary power rating for a desired power rating.
     
    10. A system for operating an aircraft gas turbine engine characterised by
    a plurality of generic aircraft operation rating structures (52 A-D) adapted to receive corresponding groups of rating information (58 A-D), wherein each of the plurality of generic aircraft operation rating structures define a specific aircraft engine thrust level;
    an input for receiving aircraft operation rating information for a selected gas turbine engine and for assigning the received aircraft operation rating information to one of the plurality of generic aircraft operation rating structures; and
    a controller (32) for accessing the groups of rating information and for producing an output communication for controlling the gas turbine engine to produce thrust corresponding to the aircraft operation rating information.
     
    11. The system as recited in claim 10, wherein the generic rating structures define logic structures (52 A-C) for accepting rating values corresponding to the selected gas turbine engine.
     
    12. The system as recited in claim 10 or 11, wherein the plurality of generic rating structures includes a corresponding plurality of generic derate structures (54 A-C) for accepting information relating to adjusting the rating information responsive to selected operating conditions.
     
    13. The system as recited in claim 10, 11, or 12, wherein the received rating information comprises one or more of a takeoff rating, a bump rating, a continuous rating, and an auxiliary power rating.
     
    14. The system as recited in any of claims 10 to 13, including a throttle input representing a desired thrust communicating with the controller such that the controller modifies the output for controlling the gas turbine engine responsive to the throttle input.
     


    Ansprüche

    1. Verfahren zum Festlegen eines Nennwertplans für eine Gasturbine, durch Folgendes gekennzeichnet:

    Festlegen einer Vielzahl von generischen Luftfahrzeugbetriebsnennwertstrukturen (52 A-D), die dazu angepasst ist, entsprechende Gruppen von Nennwertinformationen (58 A-C) zu empfangen;

    Bestimmen eines Satzes von gewünschten Luftfahrzeugbetriebsnennwerten (42 A-D) für eine ausgewählte Gasturbine, wobei die gewünschten Luftfahrzeugbetriebsnennwerte Triebwerkschubniveaus für spezifische Luftfahrzeugbetriebsbedingungen beinhalten;

    Zuordnen jedes der Sätze der gewünschten Luftfahrzeugbetriebsnennwerte zu einem entsprechenden der Vielzahl von generischen Luftfahrzeugbetriebsnennwertstrukturen;

    Generieren einer einzigartigen Luftfahrzeugbetriebsnennwertstruktur, die die gewünschten Nennwerte beinhaltet, die den generischen Luftfahrzeugbetriebsnennwertstrukturen zugeordnet sind; und

    Laden der generierten einzigartigen Luftfahrzeugbetriebsnennwertstruktur in eine Steuerung, die dazu konfiguriert ist, die ausgewählte Gasturbine gemäß der einzigartigen Luftfahrzeugbetriebsnennwertstruktur zu steuern.


     
    2. Verfahren nach Anspruch 1, beinhaltend das Festlegen eines Abweichungsplans für mindestens eine der generierten einzigartigen Nennwertstrukturen und das Laden des Abweichungsplans in die Steuerung, um der entsprechenden einzigartigen Nennwertstruktur zu entsprechen.
     
    3. Verfahren nach einem der vorstehenden Ansprüche, wobei mindestens einer der Nennwerte einen Hilfsleistungs(APR)-Nennwert umfasst.
     
    4. Verfahren nach einem der vorstehenden Ansprüche, wobei mindestens einer der gewünschten Nennwerte einen Start(MTO)-Leistungsnennwert umfasst.
     
    5. Verfahren nach einem der vorstehenden Ansprüche, wobei mindestens einer der gewünschten Nennwerte einen kontinuierlichen (MCT) Leistungsnennwert umfasst.
     
    6. Verfahren nach einem der vorstehenden Ansprüche, wobei mindestens einer der gewünschten Nennwerte einen Steigleistungs(MCL)-Nennwert umfasst.
     
    7. Verfahren nach einem der vorstehenden Ansprüche, wobei mindestens einer der gewünschten Nennwerte einen Flugleistungs(MCR)-Nennwert umfasst.
     
    8. Verfahren nach einem der vorstehenden Ansprüche, einen Abweichungswert zum Anpassen des gewünschten Nennwerts umfassend.
     
    9. Verfahren nach einem der vorstehenden Ansprüche, einen Pointer zum Kennzeichnen eines Hilfsleistungs-Nennwerts für einen gewünschten Leistungsnennwert beinhaltend.
     
    10. System zum Betreiben einer Gasturbine, durch Folgendes gekennzeichnet:

    eine Vielzahl von generischen Luftfahrzeugbetriebsnennwertstrukturen (52 A-D), die dazu angepasst ist, entsprechende Gruppen von Nennwertinformationen (58 A-D) zu empfangen, wobei jede der Vielzahl von generischen Luftfahrzeugbetriebsnennwertstrukturen ein spezifisches Luftfahrzeugtriebwerksschubniveau festlegt;

    einen Eingang zum Empfangen von Luftfahrzeugbetriebsnennwertinformationen für eine ausgewählte Gasturbine und zum Zuweisen der empfangenen Luftfahrzeugbetriebsnennwertinformationen an eine der Vielzahl von generischen Luftfahrzeugbetriebsnennwertstrukturen; und

    eine Steuerung (32), zum Zugreifen auf die Gruppen von Nennwertinformationen und zum Erzeugen einer Ausgangskommunikation zum Steuern der Gasturbine, um Schub entsprechend den Luftfahrzeugbetriebsnennwertinformationen zu erzeugen.


     
    11. System nach Anspruch 10, wobei die generischen Nennwertstrukturen logische Strukturen (52 A-C) zum Akzeptieren von Nennwert-Werten festlegen, die der ausgewählten Gasturbine entsprechen.
     
    12. System nach Anspruch 10 oder 11, wobei die Vielzahl von generischen Nennwertstrukturen eine entsprechende Vielzahl von generischen Abweichungsstrukturen (54 A-C) zum Akzeptieren von Informationen beinhaltet, die sich auf das Anpassen der Nennwertinformationen als Reaktion auf die ausgewählten Betriebsbedingungen bezieht.
     
    13. System nach Anspruch 10, 11 oder 12, wobei die empfangenen Nennwertinformationen eines oder mehrere eines Startnennwerts, eines Erschütterungsnennwerts, eines kontinuierlichen Nennwerts und eines Hilfsleistungs-Nennwerts umfassen.
     
    14. System nach einem der Ansprüche 10 bis 13, einen Drosseleingang beinhaltend, der einen gewünschten Schub darstellt und derart mit der Steuerung kommuniziert, dass die Steuerung den Ausgang zum Steuern der Gasturbine als Reaktion auf den Drosseleingang modifiziert.
     


    Revendications

    1. Procédé de définition d'un programme de calibre pour un moteur à turbines à gaz d'aéronef caractérisé par :

    la définition d'une pluralité de structures génériques de calibre de fonctionnement d'aéronef (52 A-D) conçue pour recevoir des groupes correspondants d'informations de calibre (58 A-C) ;

    la détermination d'un ensemble de calibres de fonctionnement d'aéronef souhaités (42 A-D) pour un moteur à turbines à gaz sélectionné, dans lequel les calibres de fonctionnement d'aéronef souhaités incluent des niveaux de poussée du moteur pour des conditions de fonctionnement d'aéronef spécifiques ;

    le mappage de chacun de l'ensemble de calibres de fonctionnement d'aéronef souhaités à une structure correspondante de la pluralité de structures génériques de calibre de fonctionnement d'aéronef ;

    la génération d'une structure unique de calibre de fonctionnement d'aéronef incluant les calibres souhaités mappés aux structures génériques de calibre de fonctionnement d'aéronef ; et

    le chargement de la structure unique de calibre de fonctionnement d'aéronef dans un dispositif de commande configuré pour commander le moteur à turbines à gaz sélectionné selon la structure unique de calibre d'aéronef.


     
    2. Procédé selon la revendication 1, incluant la définition d'un programme de réduction pour au moins l'un de la structure unique de calibre générée et du chargement du programme de réduction dans le dispositif de commande pour correspondre à la structure unique de calibre correspondante.
     
    3. Procédé selon une quelconque revendication précédente, dans lequel au moins l'un des calibres comprend un calibre de puissance auxiliaire (APR).
     
    4. Procédé selon une quelconque revendication précédente, dans lequel au moins l'un des calibres souhaités comprend un calibre de puissance de décollage (MTO).
     
    5. Procédé selon une quelconque revendication précédente, dans lequel au moins l'un des calibres souhaités comprend un calibre de puissance continue (MCT).
     
    6. Procédé selon une quelconque revendication précédente, dans lequel au moins l'un des calibres souhaités comprend un calibre de puissance ascensionnelle (MCL).
     
    7. Procédé selon une quelconque revendication précédente, dans lequel au moins l'un des calibres souhaités comprend un calibre de puissance de croisière (MCR).
     
    8. Procédé selon une quelconque revendication précédente, incluant une valeur de réduction pour ajuster le calibre souhaité.
     
    9. Procédé selon une quelconque revendication précédente, incluant un pointeur pour désigner un calibre de puissance auxiliaire pour un calibre de puissance souhaité.
     
    10. Système de fonctionnement d'un moteur à turbines à gaz d'aéronef caractérisé par :

    une pluralité de structures génériques de calibre de fonctionnement d'aéronef (52 A-D) conçue pour recevoir des groupes correspondants d'informations de calibre (58 A-D), dans lequel chacune de la pluralité de structures génériques de calibre de fonctionnement d'aéronef définit un niveau de poussée de moteur d'aéronef spécifique ;

    une entrée pour recevoir des informations de calibre de fonctionnement d'aéronef pour un moteur à turbines à gaz sélectionné et pour assigner les informations de calibre de fonctionnement d'aéronef reçues à l'une de la pluralité de structures génériques de calibre de fonctionnement d'aéronef ; et

    un dispositif de commande (32) pour accéder aux groupes d'informations de calibre et pour produire une communication de sortie pour commander le moteur à turbines à gaz afin de produire une poussée correspondant aux informations de calibre de fonctionnement d'aéronef.


     
    11. Système selon la revendication 10, dans lequel les structures génériques de calibre définissent des structures logiques (52 A-C) pour accepter des valeurs de calibre correspondant au moteur à turbines à gaz sélectionné.
     
    12. Système selon la revendication 10 ou 11, dans lequel la pluralité de structures génériques de calibre inclut une pluralité correspondante de structures génériques de réduction (54 A-C) pour accepter des informations relatives à l'ajustement des informations de calibre en réponse aux conditions de fonctionnement sélectionnées.
     
    13. Système selon la revendication 10, 11 ou 12, dans lequel les informations de calibre reçues comprennent un ou plusieurs d'un calibre de décollage, d'un calibre de secousse, d'un calibre continu et d'un calibre de puissance auxiliaire.
     
    14. Système selon l'une quelconque des revendications 10 à 13, incluant une entrée de commande de puissance représentant une poussée souhaitée communiquant avec le dispositif de commande de sorte que le dispositif de commande modifie la sortie pour commander le moteur à turbines à gaz en réponse à l'entrée de commande de puissance.
     




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    Cited references

    REFERENCES CITED IN THE DESCRIPTION



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    Patent documents cited in the description