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Improvements to the flight dynamics model of the PT6A-27 engine #51

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7c63a92
An experimental new version of the PT6A-27 fdm for JSBSim
ranguli Oct 14, 2024
83e10f6
XML formatting
ranguli Oct 18, 2024
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220 changes: 110 additions & 110 deletions Engines/PT6A-27.xml
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Original file line number Diff line number Diff line change
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<?xml version="1.0"?>
<!--
File: my_engine.xml
Author: AeromatiC++ v 3.2.5
See: http://wiki.flightgear.org/JSBSim_Engines#FGTurboprop
Inputs:
name: PT6A-27
type: Turboprop Engine
power: 620.0 hp
inlet temperature: 725.0 degrees C
overall pressure ratio: 15.0:1
Outputs:
psfc: 0.579 lbs/hr/hp
engine weight: 336.3 lbs
engine length: 4.9 ft
engine diameter: 1.9 ft
-->
<turboprop_engine name="PT6A-27">
<milthrust unit="LBS"> 1523.2 </milthrust>
<idlen1> 52.0 </idlen1>
<maxn1> 101.5 </maxn1>
<idlen2> 40.0 </idlen2>
<maxn1> 96.0 </maxn1>
<maxpower unit="HP"> 620.0 </maxpower>
<psfc unit="LBS/HR/HP"> 0.74 </psfc>
<n1idle_max_delay> 1.2 </n1idle_max_delay>
<maxstartingtime> 0.1 </maxstartingtime>
<startern1> 20.0 </startern1>
<ielumaxtorque unit="FT*LB"> 1536.0 </ielumaxtorque>
<itt_delay> 3.0 </itt_delay>
<betarangeend> 10.0 </betarangeend>
<reversemaxpower> 91.0 </reversemaxpower>
<function name="EnginePowerVC">
<table>
<description> Engine power, function of airspeed and pressure </description>
<independentVar lookup="row">atmosphere/P-sl-psf</independentVar>
<independentVar lookup="column">velocities/ve-kts</independentVar>
<tableData>
0 50 100 150 200 250
503 0.357 0.380 0.400 0.425 0.457 0.486
1048 0.586 0.589 0.600 0.621 0.650 0.686
1328 0.707 0.721 0.731 0.757 0.786 0.821
1496 0.779 0.786 0.808 0.821 0.857 0.900
1684 0.850 0.857 0.874 0.900 0.943 0.979
1896 0.914 0.929 0.946 0.971 1 1.057
2135 1 1.011 1.029 1.043 1.083 1.150
2213 1.029 1.043 1.057 1.079 1.114 1.171
</tableData>
</table>
</function>
<!--function name="EnginePowerVC">
<table>
<description> Engine power, function of airspeed and pressure </description>
<independentVar lookup="row">atmosphere/pressure-altitude</independentVar>
<independentVar lookup="column">velocities/ve-kts</independentVar>
<tableData>
0 250
0 1 1
25000 1 1
</tableData>
</table>
</function-->
<table name="EnginePowerRPM_N1" type="internal">
<description> Engine Power, function of RPM and N1 </description>
<tableData>
0 5 60 86 94 95 96 97 98 99 100 101
0.0 0.0 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
803.5 0.0 0.4 29.2 166.9 292.1 317.1 350.5 383.8 417.2 442.2 484.0 517.4
1203.0 0.0 0.4 25.0 192.0 333.8 358.8 392.2 421.4 458.9 492.3 534.1 567.4
1604.8 0.0 0.4 4.2 200.3 367.2 396.4 425.6 458.9 496.5 525.7 567.4 600.8
2006.5 0.0 0.1 0.1 187.7 375.5 413.0 438.1 471.4 509.0 542.4 584.1 621.7
2207.4 0.0 0.1 0.1 171.1 367.2 400.5 429.7 467.3 504.9 538.2 579.9 620.0
</tableData>
</table>
<table name="ITT_N1" type="internal">
<description> Inter-Turbine Temperature ITT [deg C] depending on N1 and engine run (0=off / 1=running) </description>
<tableData>
0 1
0 0 0
12 105 105
60 188 432
96 283 691
100 294 720
</tableData>
</table>
<table name="CombustionEfficiency_N1" type="internal">
<description>Dependency of fuel efficiency coefficient on N1 (and RPM)</description>
<tableData>
90 0.1221
91.2 0.2834
92.2 0.5336
93.4 0.7188
94.1 0.7741
95.2 0.8471
96.5 0.9001
100 1
</tableData>
</table>
</turboprop_engine>
<?xml version="1.0"?>

<!--
File: PT6A-27.xml
Author: AeromatiC++ v 3.3.21

See: http://wiki.flightgear.org/JSBSim_Engines#FGTurboprop

Inputs:
name: PT6A-27
type: Turboprop Engine
power: 620.0 hp
inlet temperature: 1713.2 degrees F
overall pressure ratio: 6.7:1

Outputs:
psfc: 0.590 lbs/hr/hp
engine weight: 336.31 lbs
engine length: 4.87 ft
engine diameter: 1.88 ft
-->

<turboprop_engine name="PT6A-27">
<milthrust unit="LBS">1388.80</milthrust>

<!--
The idle speed of the gas generator (N1) expressed as a percentage of maximum N1 RPM.
In turboprop engines like the PT6A-27, N1 refers to the gas generator speed,
which includes the compressor and turbine stages driving the compressor.
-->
<idlen1>60.0</idlen1>

<!-- The maximum allowable gas generator speed (N1) as a percentage of maximum N1 RPM. -->
<maxn1>100.0</maxn1>

<!-- The maximum shaft horsepower (shp) the engine can produce. This value of 620shp is easily verifiable online. -->
<maxpower unit="HP">620.0</maxpower>

<!-- Power Specific Fuel Consumption (PSFC), measured in pounds of fuel burned per hour per horsepower produced. -->
<psfc unit="LBS/HR/HP">0.612</psfc>

<!-- The maximum delay (in seconds) for N1 to reach idle speed during engine start-up. -->
<n1idle_max_delay>1</n1idle_max_delay>

<!-- The maximum allowable time (in seconds) for the engine to start. -->
<maxstartingtime>20</maxstartingtime>
<startern1>20</startern1>
<ielumaxtorque unit="FT*LB">1578.4</ielumaxtorque>
<itt_delay>0.05</itt_delay>
<betarangeend>64</betarangeend>
<reversemaxpower>60</reversemaxpower>

<function name="EnginePowerVC">
<table>
<description> Engine power, function of airspeed and pressure </description>
<independentVar lookup="row">atmosphere/P-psf</independentVar>
<independentVar lookup="column">velocities/ve-kts</independentVar>
<tableData>
0 50 100 150 200 250 300 350
503 0.357 0.380 0.400 0.425 0.457 0.486 0.517 0.550
1048 0.586 0.589 0.600 0.621 0.650 0.686 0.724 0.764
1328 0.707 0.721 0.731 0.757 0.786 0.821 0.858 0.896
1496 0.779 0.786 0.808 0.821 0.857 0.900 0.945 0.993
1684 0.850 0.857 0.874 0.900 0.943 0.979 1.016 1.055
1896 0.914 0.929 0.946 0.971 1 1.057 1.117 1.181
2135 1 1.011 1.029 1.043 1.083 1.150 1.221 1.297
2213 1.029 1.043 1.057 1.079 1.114 1.171 1.231 1.294
</tableData>
</table>
</function>

<table name="EnginePowerRPM_N1" type="internal">
<description> Engine Power, function of RPM and N1 </description>
<tableData>
0 5 60 86 94 95 96 97 98 99 100 101
0.0 0.0 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
803.5 0.0 0.4 29.2 166.9 292.1 317.1 350.5 383.8 417.2 442.2 484.0 517.4
1203.0 0.0 0.4 25.0 192.0 333.8 358.8 392.2 421.4 458.9 492.3 534.1 567.4
1604.8 0.0 0.4 4.2 200.3 367.2 396.4 425.6 458.9 496.5 525.7 567.4 600.8
2006.5 0.0 0.1 0.1 187.7 375.5 413.0 438.1 471.4 509.0 542.4 584.1 621.7
2207.4 0.0 0.1 0.1 171.1 367.2 400.5 429.7 467.3 504.9 538.2 579.9 620.0
</tableData>
</table>

<table name="ITT_N1" type="internal">
<description> Inter-Turbine Temperature ITT [deg C] depending on N1 and engine run (0=off / 1=running) </description>
<tableData>
0 1
0 0 0
15 248.4 248.4
60 445.4 1291.8
96 669.9 1689.2
100 695.6 1867.4
</tableData>
</table>

<table name="CombustionEfficiency_N1" type="internal">
<description>Dependency of fuel efficiency coefficient on N1 (and RPM)</description>
<tableData>
90 0.1221
91.2 0.2834
92.2 0.5336
93.4 0.7188
94.1 0.7741
95.2 0.8471
96.5 0.9001
100 1
</tableData>
</table>
</turboprop_engine>