Turbojet Deck
Contents
1. Copyright C 2013 by Joachim Kurzke pe Turbojet Deck 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 SIM ZTAMB ZMA ZWB3 ZWB3Q ZERAM1 ZERM11 SDIST FYPH FYSH ZPWSD ZTIME TIMEF1 ZIMEF2 TIMEO ZTIMET ZXJPTL ZXNSD Differentiated Options SERAM 4 Selects input values of primary and secondary ram pressure recovery SERAM 5 Selects input value of primary stream ram pressure recovery and calls user supplied subroutine ERAMX for secondary stream ram pressure recovery SERAM 6 Selects primary and secondary stream ram pressure recoveries from user supplied subroutine ERAMX Inlet mode selection SIM 1 Selects altitude and Mach number SIM 2 Selects pressure and temperatures SIM Other than 1 or 2 coordinated between user and supplier Ambient temperature Engine inlet total temperature at station 1A High pressure compressor discharge bleed flow rate High pressure compressor bleed flow ratio discharge over component inlet Free stream Mach number Primary stream ram pressure recovery Secondary stream ram pressure recovery Reserved for historical consistency Reserved for historical consistency Reserved for historical consistency Reserved for historical consistency Inlet pressure and temperature distortion selection Primary maximum response frequency Secondary maximum response frequen2. Copyright C 2013 by Joachim Kurzke Input Output There are three options offered for the ram pressure recovery selection switch SERAM 1 subsonic ZERAM as SERAM 2 supersonic ZERAM 1 0 075 XM 1 gt gt es DER ZERAM ram recovery from the intake map 7 1 1 FIXIN Parameter Definition The SAE Aerospace Standard AS681G provides a method for the presentation of results from computer programs using FORTRAN 77 The fixed sequence list of the parameters in the fixed input labeled common FIXIN and the identity ofthese parameters with typical nomenclature consistent with ARP755 are as follows 1 NIN Input file number INTEGER 2 NOUT Output file number INTEGER 3 IND Engine program indicator INTEGER 4 TITLE 18 User title dimension 18 HOLLERITH 5 CASE Numerical case identification 6 ALT Geopotential pressure altitude 7 ZDTAMB Ambient temperature minus standard atmospheric temperature 8 ZDT1A Temperature to be added to T1A 9 ZERM1A Ram pressure recovery at station 1A 10 ZPWXH Customer high pressure rotor power extraction 11 ZPAMB Ambient pressure 12 ZPC Power code 13 ZPLA Power lever angle 14 ZP1A Engine inlet total pressure at station 1A 15 ZRC Rating code 16 SERAM Ram pressure recovery selection Average Options SERAM 1 Selects specified ram pressure recovery SERAM 2 Selects input value of ram pressure recovery SERAM 3 Selects ram pressure recovery from user supplied subroutine ERAMX
3. and Nidle corresponds to rel N for PLA 0 Copyright C 2013 by Joachim Kurzke Engine Program Performance Options 15 N max Power Nudie 0 100 Idle Max Power Power Lever Angle PLA 6 3 Power Code The following Power Codes are defined PC 50 Maximum PC 20 Idle PC 0 Power Lever Angle input is active however any valid Rating Code input ZRC overrules the Power Lever Angle input PC 1 run to net thrust ZFN control system active PC 2 run to fuel flow ZWF control system active except fuel flow schedule PC 3 run to spool speed ZXNRPM control system active PC 11 run to net thrust ZFN control system inactive PC 12 run to net fuel flow ZWF control system inactive PC 13 run to spool speed ZXNRPM control system inactive Copyright C 2013 by Joachim Kurzke 16 Turbojet Deck 6 4 7 1 Rating Code There are two valid Rating Codes defined 1 Rating code ZRC 50 selects maximum power 2 ZRC 20 selects idle Input Output The input and output data are arranged in four groups that correspond with the COMMON blocks FIXIN VARIN FIXOUT and VAROUT as defined in AS681 FIXIN FIXIN properties are as defined in AS681 Some of them are not applicable some of them are not used in the Turbojet Deck Note that all data that are transferred to the functions and procedures in the DLL are of the type double There are two inlet modes selectable with the switch SIM
4. e a spool speed input as a function of time 10 Identification and Revision Procedure The version of the DLL can be read by calling the function GetDLLVersion The responsibility for the data is with the provider of the Engine Model File 11 References 1 SAE AEROSPACE STANDARD AS681 Rev G 1996 2 J Kurzke GasTurb 12 User Manual 2012 Copyright C 2013 by Joachim Kurzke Index C Call Parameters 8 Call Sequence 9 Convergence Problems 26 Cycle Reference Point 26 D Data Directory 7 Data Input and Output 16 Delphi 7 8 Delphi Test Main 11 DLL Directory 7 DLL Initialization 9 DLL Interface 8 E Engine Model File 7 13 Excel 7 8 Excel Application 11 F File Organization 7 FIXIN 8 16 FIXIN Parameter Definition 17 FIXOUT 8 19 FIXOUT Parameter Definition 20 Fuel Flow Given 15 Function 8 Os GetDLLVersion 8 27 DN Idle 15 16 Initialization 9 InitializeEngine 8 9 Intake Map 13 Interface 8 Iteration Variable 26 L Limiter codes steady state 24 Limiter codes transient 25 Limiters 13 Copyright C 2013 by Joachim Kurzke M Maximum Power 15 16 Messages 23 N Nomenclature Stations 11 NSI 23 Numerical Status Indicator 23 P PathtotheDLL 8 PLA 14 PLA Definition 13 Power Code 15 Power Lever Angle 14 Procedure 8 R Rating Code 15 16 References 27 Sa SERAM 16 SEST 9 19 26 SIM 16 SinglePoint 8 9 SMode 13 Spool Speed Given 15 Statio
5. varies the variables iteratively in such a way that all the conditions are fulfilled when the calculation is finished Sometimes the iteration fails to converge which is indicated by NSI 9100 Non convergence can have many reasons sometimes one or the other of the normal input properties are unreasonable sometimes the start values of the iteration variables are far away from those of the solution sometimes the solution requires one or more components operating far outside of their respective component maps In this computer deck the output values of the iteration variables are BTAC RXNH BTAT and DTRC in the VAROUT group While SEST is zero these values are employed as estimates for the next point to be calculated If a point has not converged then most probably the values of BTAC RXNH BTAT and DTRC are unreasonable and not suited as estimate for the next case to be calculated For recovering from this situation SEST can be set to 1 which makes the iteration begin with the values ZBTAC ZXNH ZBTAT ZDTRC from the VARIN group If the iteration fails to converge because the operating conditions between two steady state points are very different an idle case followed by a max rating case for example then the problem can be avoided eventually by introducing a few intermediate rating steps Convergence problems that are not understood can be examined with GasTurb 12 In this program there are many more diagnostic options available than in t
6. 1 XN_HPC 100 60 0 002 alt This composed value is employed as a Min Limiter with the min value of 1 0 Transient Limiters During transient operation with the GasTurb 12 control system active all the steady state limiters are activated as set in the Engine Model File Additionally the transient limiters like dN dtmin and dN dtmax for example are active If you want dN dtmax make a function of spool speed for example then you must employ an additional iteration combined with a composed value The definitions of the composed value for transient operation and the iteration can be accessed from the menu in the transient window of GasTurb 12 In the Engine Model File delivered as an example for the Turbojet Deck application dN dtmax is a function of spool speed The first composed value for transient operation is defined as cp_val1 0 2 0 15 XN_HPC The input value for dN dtmax is iterated in such a way that it equals cp_val1 For running the simulation with modified limiter settings a new Engine Model File must be created Power Lever Angle The power level selection is controlled by the input value for the Power Code ZPC If ZPC is 0 then the Power Lever Angle input ZPLA will be used However any valid Rating Code ZRC will overwrite the ZPLA input In the Turbojet Deck the power lever angle is linearly connected with the spool speed Nmax Power is equal to rel N for PLA 100 as defined on the Transient Input Page of GasTurb 12
7. 2FO XNHFO ALTFO PAMBFO PLAFO P1AFO TAMBFO TIAFO XMFO SMHFO TIMEFO ERAM1FO DTAMBFOX PCFOH RCFO WB3FO WB3QFO PWXHFO Declare Sub ReadVAROUT Lib Path to the DLLATurbojetDeckLib dll humidVO T2VO T3VO TAVO T41VOF TSVOH P3VO Ps3VO P5VO NHDOT FAR4 LIMCD BTACVO RXNHVO BTATVO DTRCVO Declare Sub InitializeEngine Lib Path to the DLLATurbojetDeckLib dll ByVal DLLPath ByVal Filename Declare Sub SinglePoint Lib Path to the DLLATurbojetDeckLib dll DLL Initialization During initialization of the DLL the files in the DLL directory and in the Engine Model File directory are read Furthermore the cycle reference point is calculated which yields all the output quantities for this operating condition After the call of InitializeEngine all the elements of FIXIN VARIN FIXOUT and VAROUT can be read by the DLL calling program Initialize Engine ReadFIXIN Copyright C 2013 by Joachim Kurzke IKA Turbojet Deck ReadVARIN ReadFIXOUT ReadVAROUT If after the initialization the VARIN propertv SEST is set to 1 then the following single point calculation will emplov as starting values of the iteration the properties ZBTAC ZRXNH ZT4 ZBTAT and ZDTRC It is a good idea to write the results i e the VAROUT properties BTAC RXNH BTAT and DTRC to the corresponding input properties immediately after calling InitializeEngine Thus there are reasonable estimate
8. ET 26 3 TraNSIEMU an ee SE NENNEN Se EE EN EE d 27 Part X Identification and Revision Procedure 27 Part XI References 27 Index 29 Copyright C 2013 by Joachim Kurzke GasTurb Computer Deck GasTurb Computer Deck The GasTurb Turbojet Deck is a computer deck as defined in the SAE Aerospace Standard AS681 The actual engine subroutine is contained in a Dynamic Link Library DLL The use ofthe engine subroutine is demonstrated both with a Delphi test main program and with an Excel macro The Dynamic Link Library can be used with any other 32 bit Windows program The data describing the engine are created with GasTurb 12 as an Engine Model File which is loaded during the Turbojet Deck initialization process The Engine Model File contains all data necessary for doing off design simulations both for steady state and transient operation Maximum and minimum limiters as well as bleed schedules must be defined in the engine model It is strongly recommended to check this model thoroughly with GasTurb 12 before using it with the Turbojet Deck DLL Transient simulations can employ the control system as defined in the GasTurb 12 model or run to a specified fuel flow or spool speed Engine Description With this generic computer deck the performance of single spool turbojet engines without afterburner can be calculated Which engine is modeled in particular depends on the Engine Model File created with GasTurb 12 Program Description The Tu
9. GasTurb A Turbojet Deck Joachim Kurzke Turbojet Deck Steady State Performance by Joachim Kurzke Turbojet Deck Copyright C 2013 by Joachim Kurzke All rights reserved No parts of this work may be reproduced in any form or by any means graphic electronic or mechanical including photocopying recording taping or information storage and retrieval systems without the written permission of the publisher Products that are referred to in this document may be either trademarks and or registered trademarks of the respective owners The publisher and the author make no claim to these trademarks While every precaution has been taken in the preparation of this document the publisher and the author assume no responsibility for errors or omissions or for damages resulting from the use of information contained in this document or from the use of programs and source code that may accompanyit In no event shall the publisher and the author be liable for any loss of profit or any other commercial damage caused or alleged to have been caused directly or indirectly by this document Printed in Germany Contents 5 Table of Contents Part GasTurb Computer Deck 7 Part Il Engine Description 7 Part Ill Program Description 7 Part IV Program Setup 7 A PA 7 2 DLL Tu EE 8 3 DLL Function Call Sequence soii ica ii i EO EA fitt 9 4 Test Main OO 11 5 Excel Applica ti n iii ii iii i ee dE Eege EES 11 Part V Nomenclature and Un
10. ckLib dll BvVal ZHUMIDVI BvVal ZFHVVI BvVal ZENVIH ByVal ZWFVI ByVal ZXNRPMVI ByVal ZWRCO2VIH ByVal SESTVI ByVal ZBTACVI ByVal ZRXNHVI ByVal ZTAVI ByVal ZBTATVI ByVal ZDTRCVI ByVal STRANSVI ByVal ZCTRCPVI ByVal ZCTRCDVI ByVal ZCTRCIV Et Copyright C 2013 by Joachim Kurzke Program Setup 9 4 3 procedure ReadVARIN var ZHUMIDVI ZFHVVI ZFNVI ZWFVI ZXNRPMVI ZWRCQ2VI SESTVI ZBTACVI ZRXNHVI ZTAVI Z BTATVI ZDTRCVI STRANSVI ZCTRCPVI ZCTRCDVI ZCT RCIVI double procedure ReadFIXOUT var NSIFO AE8FO FRAMFO FGFO FHVFO FNFO PB3FO P7FO SFCFO TB3FO T7FO WFEFO W FTFO W1AFO W7FO W2FO XNHFO ALTFO PAMBF O PLAFO P1AFO TAMBFO T1AFO XMFO SMHFO TIMEF O ERAM1FO DTAMBFO PCFO RCFO WB3FO W B3QFO PWXHFO Double procedure ReadVAROUT var humidVO T2VO T3VO T4VO T41VO T5VO P3VO Ps3VO P5VO NHDOT FAR4 LIMCD BTA CVO RXNHVO BTATVO DTRCVO Double procedure InitializeEngine DLLPath FileName PChar procedure SinglePoint DLL Function Call Sequence Declare Sub ReadVARIN Lib Path to the DLLATurbojetDeckLib dll ZHUMIDV IE ZFHVVI ZFNVI ZVVFVI ZXNRPMVIH ZWRCO2VI SESTVI ZBTACVI ZRXNHVI ZTAVI ZBTATVI ZDTRCVI STRANSVI ZCTRCPVI ZCTRCDVI ZCTRCIVI Declare Sub ReadFIXOUT Lib Path to the DLLATurbojetDeckLib dll NSIFO AE8FO FRAMFO FGFOF FHVFO FNFO PB3FO P7FO SFCFO TB3FO T7FO WFEFO WFTFO W1AFO W7FO W
11. cy Specified shaft power Time from start of transient case Time at which frequency is changed to FYSH Time at which frequency is changed to FYPH Output time interval Termination time of transient case Polar moment of inertia of power turbine load Specified shaft rotational speed Copyright C 2013 by Joachim Kurzke Input Output IKUN 40 ZIRQSD Specified shaft torque 41 SWIND Windmilling selection 7 2 VARIN SEST O begin the iteration with the values from previous point A begin the iteration with ZBTAC ZXNH ZBTAT ZDTRC ZBTAC beta value in the compressor map ZRXNH relative spool speed ZBTAT beta value in the turbine map ZDTRC temperature increase due to recirculating bleed air ZFN specified net thrust ZWF specified fuel flow ZXNRPM specified spool speed in RPM STRANS 1 Transient with ZPLA f ZTIME input the GasTurb control system is active 2 Transient with ZWF f ZTIME input the GasTurb control system is inactive 3 Transient with ZXNRPM f ZTIME input the GasTurb control system is inactive ZCTRCP proportional constant of the GasTurb PID controller ZCTRCD differential constant of the GasTurb PID controller ZCTRCI integral constant of the GasTurb PID controller 7 3 FIXOUT FIXOUT properties are as defined in AS681 Some of them are not applicable some of them are not used in the Turbojet Deck Note that all data that are transferred from the functions and procedures in the DLL are of the type doub
12. his computer deck If non of the advice given above helps then it might be that no solution exists This can be the case for excessive power or bleed off take for example If in transient simulations a convergence problem shows up while one of the input properties changes significantly in a very short time then the time step might be too big This is similar to the case when the spool speed input while STRANS 3 implies excessive Ndot dN dt values If during a transient simulation the iteration converges after having failed at one or a few prior time steps then the convergence problem can mostly be ignored Test Cases Cycle Reference Point During initialization of the DLL the GasTurb cycle reference point is written to the input i e FIXIN and VARIN and the output FIXOUT and VAROUT groups Steady State Off Design The performance point to be calculated is defined by the data given in FIXIN and VARIN Fora steady state point ZTIME must be set to zero Copyright C 2013 by Joachim Kurzke Test Cases 9 3 Transient A transient simulation is performed if the FIXIN property ZTIME has a positive value greater than the FIXOUT property TIME from the previously calculated point Three examples are selectable in the test main program respectively in the Excel sheet e a 10 step increase in fuel flow which demonstrates the fuel flow input option STRANS 2 e aPLA maneuver with a slam deceleration followed by a slam acceleration
13. id not converge Copyright C 2013 by Joachim Kurzke 24 Turbojet Deck 9199 9201 9202 9203 9204 9210 9290 9291 9292 9293 Severe computing problem SIM must be 1 or 2 ZP1A ZT1A or ZPAMB 0 while SIM 2 SIM 2 can not be combined with SERAM 3 SERAM must be 1 2 or 3 ZRC not defined Power Lever Angle PLA definition error Engine model error SMode must be equal to 1 STRANS must be 1 2 or 3 during transient operation TIME gt ZTIME is not permitted 8 2 Steady State Limiter Codes During steady state simulations the following limiter codes are used 5 4 3 2 11 cp_val_min3 cp_val_min2 cp_val_min1 WF_min NH_min NH_max NHR_max T3_max P3_max T41_max T5_max cp_val_max1 value of the third cp val min limiter value ofthe second cp_val min limiter value of the first cp_val min limiter min fuel flow min gas generator spool speed operation within limits or no limiters activated max high pressure spool speed max corrected high pressure spool speed max burner inlet temperature max burner inlet pressure max stator outlet temperature SOT max turbine exit temperature value of the first cp_val max limiter Copyright C 2013 by Joachim Kurzke Program Messages 25 12 cp_val_max2 13 cp_val_max3 8 3 Transient Limiter Codes value of the second cp_val max limiter value of the third cp_val max limiter During transient simulations the limi
14. its 11 Station Designation disi res 22m a L e da IE aa tn 11 2 U p l I da hir 13 Part VI Engine Program Performance Options 13 st 13 Steady State Limitor Si i iii i ra ae A A ra eaaa dra O Aae a a A aaea aa aa E aee eaa aai 14 Transient Limiters inertes 14 2 Power Lever ue UE 14 3 Power Code iso iu aset eege e nenn nn nen anna nie secant L Da a ona E 15 A Rating Code ege von shue rin sats EEN v ehe s ererat st vs EE e se st morin shot ENEE KE 16 Part VII Input Output 16 1GFIXIN BEE 16 FIXIN Parameter Definition ic cova s s vde s c s ev no de san nd en ve s n s s G er n s ser tan vo SESS apenaii eseni rese ied bio li pot soset 17 2 VARIN ME 19 3 FAOUT A A A neath I DAD na 19 FIXOUT Parameter Definition 2 2 420 2 s ns s s ns or d ned ts nde ce ene So st p s s r Eugen 20 A VARQUT i a da d 23 Part VIII Program Messages 23 1 Numerical Status Indicator NSI ss nn ee te nese ente teme ee nese vente temes eee ERR EEN EE 23 2 Steady State Limiter Codes 0 sess enter eee ete nenet e tere ee tete meme tete meme teren eee ee tere mese nenet 24 3 Transient Limiter Codes iii een 25 4 About Convergence Problems sr nr rete nenn nenn nenn tete 26 Part IX Test Cases 26 Copyright C 2013 by Joachim Kurzke 6 Turbojet Deck 1 Cycle Reference Poltica ek pa de sh q dur dh dd dat shesesh doket 26 2 Steady State Off Design
15. le Copyright C 2013 by Joachim Kurzke Turbojet Deck 25 4526 not used 14283 9 nja nja nja 0 FIXOUT Parameter Definition The SAE Aerospace Standard AS681G provides a method for the presentation of results from computer programs using FORTRAN 77 The fixed sequence list of the parameters in the fixed output labeled common FIXOUT and the identity of these parameters with typical nomenclature consistent with ARP755 are as follows 1 CLASS 6 Engine program security classification Dimension 6 HOLLERITH 2 IDENT 36 Engine program titles Dimension 36 HOLLERITH Copyright C 2013 by Joachim Kurzke Input Output 21 3 NSI 10 Numerical Status Indicator Dimension 10 INTEGER 4 AE8 Primary exhaust nozzle throat effective area 5 AE18 Bypass exhaust nozzle throat effective area 6 ANGBT Boat tail angle 7 FRAM Ram drag 8 FG Gross thrust 9 FGI Ideal gross thrust 10 FG19 Bypass stream gross thrust 11 FGI19 Bypass stream ideal gross thrust 12 FHV Fuel lower heating value 13 FN Net thrust 14 PB3 High pressure compressor discharge bleed flow total pressure 15 P7 Primary exhaust flow total pressure 16 P17 Bypass exhaust flow total pressure 17 SFC Specific fuel consumption 18 Reserved for historical consistency 19 TB3 High pressure compressor discharge bleed flow total temperature 20 TC Control temperature cockpit display 21 T7 Primary exhaust flow total temperature 22 T17 Bypass exhau
16. ns 11 Steady State Performance 26 STRANS 19 26 Subroutine 8 T Test Main Delphi 11 Test Main Excel 11 Thrust Given 15 Transient Simulations 27 V VARIN 8 19 VAROUT 8 23 VBA 8 11 Vista 7 Visual Basic for Applications 8
17. odel File Both rel N for PLA 0 and rel N for PLA 100 must be set to reasonable values The input for these two quantities is found on the Transient Input Page in the Off Design Input window of GasTurb 12 Steady state limiters must be switched on both min and max limiters must be defined If transient limiters are not constant then the respective iteration must be defined The input of this iteration and the required composed values is selectable from the transient input window An intake map must be read from file before writing the Engine Model File from within GasTurb 12 This intake map however needs not necessarily be employed in the calculation SMode must be set to 1 Copyright C 2013 by Joachim Kurzke ta Turbojet Deck 6 1 1 6 1 2 6 2 Steady State Limiters Limiters can be single valued or follow a schedule How to employ control schedules is described in the GasTurb 12 help system and the manual Besides the pre defined limiters up to three composed values can be employed as additional limiters Note that drop down lists with composed values on the bottom left side of the limiter input page in GasTurb 12 will appear only if at least one composed value is defined In the Engine Model File delivered as an example for the Turbojet Deck application the idle spool speed is a function of altitude Nidle 60 0 002 Altitude The first composed value for steady state off design operation is defined as cp_val
18. rbojet Deck has been developed with Delphi XE4 running under Windows 8 The test main program has a standard windows user interface and calls functions from the Turbojet Deck DLL which contains the actual engine simulation model An alternative use of the Turbojet Deck is shown as an Excel application in the file TurbojetDeckDemo xlIs Program Setup General The Turbojet Deck calls functions from a DLL which can be used with any Windows program In the test main program this DLL is employed by a Delphi program in the file TurbojetDeckDemo xls the functions of the DLL are called from an Excel macro Before commencing with the engine simulation the functions in the DLL must be initialized During initialization an Engine Model File created with GasTurb 12 is read from file and evaluated The required organization of the files is as summarized in the table below Note that the Data Directory can be the same as the DLL Directory DLL Directory Data Directory TurbojetDeckLib DLL An Engine Model File created with GasTurb 12 LoadOptions NMS Component map data files referenced in the Engine Model File Turbojet NMS Fuels gtb and all files referenced in Fuels gtb Copyright C 2013 by Joachim Kurzke e Turbojet Deck 4 2 DLL Interface The DLL contains the functions and procedures subroutines listed in the table Note that when declaring the functions and subroutines in a VBA program within Excel for example the expression Path to
19. s for the iteration variables readily available for the use with SEST 1 if convergence problems are encountered Using the DLL for steady state simulations The procedure subroutine SinglePoint calculates a single cycle point either in steady state ZTIME 0 or transient mode ZTIME gt 0 Before calling the actual simulation function SinglePoint the input data stored in the FIXIN and VARIN properties must be transferred to the DLL by calling the procedures WriteFIXIN and WriteVARIN After the cycle calculation is finished the results can be read from the DLL by calling the procedures ReadFIXOUT and ReadVAROUT WriteFIXIN WriteVARIN SinglePoint ReadFIXOUT ReadVAROUT humid T2 T3 T4 T41 T5 P3 Ps3 P5 NHDOT FAR4 LIMCD BTAC RXNH BTAT DTRC Using the DLL for transient simulations The procedure subroutine SinglePoint calculates a single point in transient mode for the time ZTIME defined in FIXIN which must be greater than the value TIME defined in VAROUT of the previously calculated point The begin of the transient maneuver is the operating condition that was calculated with ZTIME 0 immediately before ZTIME is set to a value greater than zero ZTIME 0 repeat WriteFIXIN WriteVARIN SinglePoint ReadFIXOUT ReadVAROUT ZTIME TIME delta time until ZTIME gt end time Copyright C 2013 by Joachim Kurzke Program Setup 11 44 Test Main The Test Main program has been created and compiled with Delphi XE4 It pro
20. st flow total temperature 23 WFE Engine fuel flow rate 24 WFT Total fuel flow rate 25 W1A Engine inlet flow rate at station 1A 26 W7 Primary exhaust flow rate 27 W17 Bypass exhaust flow rate 28 W2_ High pressure compressor inlet flow rate The full number representing the relevant station designation e g W21 W215 W2A will be defined by the program supplier 29 XNH High pressure rotor rotational speed 30 XNI Intermediate pressure rotor rotational speed 31 XNL Low pressure rotor rotational speed Copyright C 2013 by Joachim Kurzke 22 Turbojet Deck 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 XNSD ALT ERAM1A PAMB PLA P1A TAMB TIA XM SML SMI SMH PWSD TIME TRQSD ERAM1 ERAM11 DTAMB DT1A PC RC WB3 WB3Q Delivered shaft rotational speed Geopotential pressure altitude Ram pressure recovery at station 1A Ambient pressure Power lever angle Engine inlet total pressure at station 1A Ambient temperature Engine inlet total temperature at station 1A Free stream Mach number Low Pressure Compressor Surge Margin Intermediate Pressure Compressor Surge Margin High Pressure Compressor Surge Margin Reserved for historical consistency Reserved for historical consistency Delivered shaft power Output Time from start of transient case Delivered shaf
21. t torque Primary stream ram pressure recover Secondary stream ram pressure recover Reserved for historical consistency Reserved for historical consistency Reserved for historical consistency Reserved for historical consistency Ambient temperature minus standard atmosphere temperature Temperature added to T1A Power code Rating code High pressure compressor discharge total bleed flow rate Resultant from combined inputs no 20 and 21 of FIXIN High pressure compressor total bleed flow ratio discharge over component inlet Copyright C 2013 by Joachim Kurzke Input Output 23 Resultant from combined inputs no 20 and 21 of FIXIN 61 PWXH Customer high pressure rotor power extraction ZA VAROUT humid relative humidity T2 compressor inlet temperature T3 compressor exit temperature T4 burner exit temperature T41 turbine stator exit temperature T5 turbine exit temperature P3 compressor exit pressure PS3 compressor exit static pressure P5 turbine exit pressure NHDOT spool speed change per second FAR4 bumer fuel air ratio LIMCD limiter code BTAC beta value in the compressor map RXNH relative spool speed BTAT beta value in the turbine map DTRC temperature increase due to recirculating bleed air 8 Program Messages 8 1 Numerical Status Indicator NSI The following Numerical Status Indicator values are defined 0 Valid result 600 A component map was extrapolated 1600 Surge margin lt 0 9100 Calculation d
22. ter code LIMCD in VAROUT can have the following values 0 1 Control 2 N 3 N corr 4 T3 5 P3 6 T41 7 T5 8 cp_val_max1 9 cp_val_max2 10 cp_val_max3 11 N_dot_max 12 far max 13 WF P3 max 14 WF max 15 N_dot_min 16 far_min 17 WF P3 min 18 Nmin 19 WF min 20 cp val mini 21 cp val min2 22 cp val min3 Copyright C 2013 by Joachim Kurzke control system svvitched off operation vvithin limits max spool speed max corrected spool speed max burner inlet temperature max burner inlet pressure max stator outlet temperature SOT max turbine exit temperature max composed value 1 max composed value 2 max composed value 3 max dN dt acceleration max fuel air ratio acceleration max WF P3 acceleration max fuel flow min dN dt deceleration min fuel air ratio deceleration min WF P3 deceleration min spool speed min fuel flow min composed value 1 min composed value 2 min composed value 3 Turbojet Deck 8 4 9 2 About Convergence Problems Any off design gas turbine performance simulation program requires iteration That means that the values of some variables must be estimated at the beginning of the calculation Corresponding with the number of iteration variables there is an equal number of conditions within the mathematical model of the gas turbine While the iteration variables do not hawe their correct value then some or all of the conditions are not fulfilled A sophisticated algorithm
23. th information which is valid only on the computer of the DLL author with the path to the place where you have stored the DLL on your computer The calculation options in the Excel file are essentially the same as those in the Test Main program 5 Nomenclature and Units 5 1 Station Designation The station definition used in the program follovvs the international standard for performance computer programs This standard has been published by the Society of Automotive Engineers SAE as ARP 755C Copyright C 2013 by Joachim Kurzke Turbojet Deck Recirculating 0 HPT Cooling 5 Overboard Handling Bleed Bleed Okg s 0 1 The thermodynamic station names are defined as follows ambient aircraft engine interfac first compressor inlet last compressor exit cold side heat exchanger inlet burner inlet burner exit first turbine stator exit rotor inlet turbine exit after addition of cooling air jet pipe inlet reheat entry nozzle throat nozzle exit convergent divergent nozzle only Copyright C 2013 by Joachim Kurzke Nomenclature and Units 13 5 2 Units The functions and procedures in the DLL employ SI units 6 Engine Program Performance Options 6 1 Engine Model File The Engine Model File that is read during the initialization of the DLL must have been be created with GasTurb 12 The following restrictions apply SI units must be selected when writing the Engine M
24. the DLL in the table below must be replaced by the actual path to the DLL on the users machine function GetDLLVersion double procedure WriteFIXIN ZCASEFI ZALTFI ZDTAMBFI ZERMIAFI ZPVVX HFI ZPAMBFI ZPCFI ZPLAFI ZP1AFI ZRCFI SERAMFI SIMFI ZTAMBFI ZT1AFI ZWB3FI ZWB3QFI ZXM FI ZTIMEFI double procedure ReadFIXIN var ZCASEFI ZALTFI ZDTAMBFI ZERMIAFI ZPWXHFI ZPAMBFI ZPCFI ZPLAFI ZP1AFI ZRC FI SERAMFI SIMFI ZTAMBFI ZT1AFI ZWB3FI ZW B3QFI ZXMFI ZTIMEFI double procedure WritevARIN ZHUMIDVI ZFHVVI ZFNVI ZVVFVI ZXNRPMVI ZWRCQ2VI SESTVI ZBTACVI ZRXNHV1 ZT4VI ZBTATVI ZDTRCVI STRANSVI ZCTRCPVI ZCTR CDVI ZCTRCIVI double Visual Basic for Applications VBA Declare Function GetDLLVersion Lib Path to the DLLXTurbojetDeckLib dll As Double Declare Sub WriteFIXIN Lib Path to the DLLATurbojetDeckLib dll ByVal ZCASEFI ByVal ZALTFI ByVal ZDTAMBFI ByVal ZERM1AFI ByVal ZPWXHFI ByVal ZPAMBFH BvVal ZPCFI ByVal ZPLAFI BvVal ZPIAFI ByVal ZRCFI ByVal SERAMFI ByVal SIMFI ByVal ZTAMBFI ByVal ZT1AFI ByVal ZWB3FIH ByVal ZVVB3QFI ByVal ZXMFIH ByVal ZTIMEFI Declare Sub ReadFIXIN Lib Path to the DLLATurbojetDeckLib dll ZCASEFI ZALTFI ZDTAMBFH ZERM1AFH ZPWXHFI ZPAMBFI ZPCFI ZPLAFI ZP1AFI ZRCFI SERAMFI SIMFI ZTAMBFI ZTIAFI ZWB3FIH ZWB3QFIH ZXMFIH ZTIMEFIH Declare Sub WriteVARIN Lib Path to the DLLATurbojetDe
25. vides a graphical user interface for the functions and procedures in the DLL Before commencing with simulations the DLL must be initialized by loading an Engine Model File which was created with GasTurb 12 Note that the component maps employed in the Engine Model File must be stored in the same directory as the Engine Model File as described on the general introduction to the program setup On the steady state input page the input properties for a single point are offered The input properties are grouped as FIXIN and VARIN the output properties are shown in the groups FIXOUT and VAROUT The transient page of the test main program offers the following three simulation examples e A step increase of 10 in fuel flow GasTurb 12 control system inactive e A PLA maneuver with activated control system as described with the Engine Model File e An example with prescribed spool speed GasTurb 12 control system inactive Each transient maneuver commences with the steady state condition calculated before switching to transient simulations 45 Excel Application The file TurbojetDeckDemo xls which is delivered as part of the software package demonstrates the use ofthe Turbojet Deck DLL with Excel Before running the file TurbojetDeckDemo xls make sure that the correct path to the DLL is introduced in the declaration section of the VBA program After starting Excel macros activated use Alt F11 for opening the VBA editor and replace the DLL pa
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