PT6A Engine Testing

PT6A SERIES ENGINE TESTING

PREPARED BY : JOKO ISMIYANTO

PT. PT. NUSANT N USANTARA ARA TURBIN T URBIN & PROPULSI PROPUL SI 2013

1

PT6A SERIES ENGINE TESTING TABLE OF CONTENT

1. ENGI ENGINE NE TEST TEST FLOW FLOW CHAR CHART T

…………………………………………………………………. 3

2. TEST TEST REQUI REQUIREM REMENT ENT AND AND PROCE PROCEDUR DURE E MATRIX MATRIX

…………………….……………………. 5

3. LIST LIST OF OF PT6A PT6A PARA PARAMET METER ER AND AND SYMB SYMBOL OL

…………………….……………………. 6

4. TEST TEST PROC PROCEDU EDURE RE SEQU SEQUENC ENCE E

…………………….……………………. 7

5. ENGINE ENGINE TEST TEST OPERA OPERATIN TING G CONDITI CONDITION ON LIMIT LIMIT

…………………….……………………. 9

6. ENGINE ENGINE MOT MOTORI ORING, NG, ST STARTING ARTING AND AND SHUT SHUT DOWN DOWN

…………………….……………………. 10

7. RUN RUN IN IN PR PROCED OCEDUR URE E

…………………….……………………. 12

8. ACCESSORI ACCESSORIES ES GEARBOX GEARBOX (AGB) (AGB) VIBRA VIBRATION TION SURVEY SURVEY

…………………….……………………. 13

9. REDUCT REDUCTION ION GEARB GEARBOX OX (RGB) (RGB) VIBRA VIBRATIO TION N CHECK CHECK

…………………….……………………. 15

10. ACCELERATION ACCELERATION AND BODIE CHECK CHECK

…………………….……………………. 16

11. TT5 TRIM DETERMINA DETERMINATION TION

…………………….……………………. 21

12. ACCEPTANCE ACCEPTANCE CHECK CHECK (PERFORMANCE)

…………………….……………………. 26

13. CONTROL CONTROL SETTING : MAXIMUM MAXIMUM NG ADJUSTMENT ADJUSTMENT

…………………….……………………. 56

14. CONTROL CONTROL SETTING : MINIMUM FUEL FLOW FLOW CHECK CHECK

…………………….……………………. 60

15. POST TEST TEST RUN RUN CHECK CHECK

…………………….……………………. 64

16. UNUSUAL UNUSUAL OIL CONDITIO CONDITION N

…………………….……………………. 66

2

PT6A series engine testing

ENGINE TEST PROCESS FLOW CHART START INSPEKSI VISUAL DAN CEK KELENGKAPAN DOKUMEN

QI TC17-002

ENGINE & DOKUMEN KOMPLIT

TIDAK

KONTAK PPC

YA PREPARASI ENGINE & FASILITAS

QI TC17-002 dan OVERHAUL MANUAL

CHECK ENGINE & FASILITAS TEST : CEK KEWAJARAN NILAI ZERO READING PARAMETER CEK SISTEM PROTEKSI CEK FUNGSI KONTROL DYNO


•

• •

FASILITAS TEST NORMAL

TIDAK

KONTAK FUNGSI ETS

YA TEST ENGINE


EVALUASI HASIL TEST


A

3


ENGINE TEST PROCESS FLOW CHART

A BELLMOUTH & EXHAUST CHECK


DE-PREPARASI ENGINE


LENGKAPI DOKUMEN TEST


KONTAK PPC

FINISH

4


TEST REQUIREMENT & PROCEDURE MATRIX PARAGRA F NO.

PROCEDURE

GAS POWER ENGINE GENERATO SECTIO R N

1

General

X

X

X

2

Consumable material

X

X

X

3

Special tools

X

X

X

4

Fixtures, equipment and supplier tools

X

X

X

5

Engine test equipment

X

X

X

7

Symbols

X

X

X

8

Preparation for test

X

X

X

9

Engine motoring, starting & shut down

X

X

X

10A

LIMITS

X

X

X

10D

Preliminary check

X

X

X

10E

AGB vibration survey

X

X

10G

Acceleration and Bodie check

X

X

10H

TT5 trim determination

X

X

10I

Acceptance check / performance check

X

X

10J

Acceptance Value

X

X

11A

X

X

11C

Control setting : Minimum Governor check Control setting : Propeller Governor maximum speed Control setting : Underspeed fuel governing check

11D

Control setting : Maximum NG adjustment

X

X

11E

Control setting : Minimum Fuel Flow Check

X

X

12

Post test run check

X

X

13

Unusual oil condition

X

14

Preservation

X

X

15

Removal of test equipment

X

X

X

18

Final check

X

X

X

11B

X

X

X

X

19 Power section run – in X Note : The vibration survey requirement applies only to engine being tested following overhaul or repair requiring balancing of the compressor rotor assembly

5


LIST OF PT6A PARAMETER AND SYMBOL During static condition / engine not running / zero reading , the normal reading for parameters are listed below: SYMBOLS COMPUTER DYNOSP WFPPH NGPER

PARAMETER NAME

OHM Wf

NORMAL VALUE @ ZERO READING VALUE UNIT

Dyno speed Fuel flow Gas generator speed in percent

0 0 0

rpm pph %

NG NFPER

Ng

Gas generator speed in radian per minute Power turbine speed in percent

0 0

rpm %

NF TT11 TT12 TT13 TT14 TT1A TT5 TT71 TT72 TT73 TT74 TT75 TT76 TT77 TT78

Nf

Power turbine speed in radian per minute Engine inlet temperature no 1 Engine inlet temperature no 2 Engine inlet temperature no 3 Engine inlet temperature no 4 Engine inlet temperature average Interturbine temperature Engine exhaust nozzle temperature no. 1 Engine exhaust nozzle temperature no. 2 Engine exhaust nozzle temperature no. 3 Engine exhaust nozzle temperature no. 4 Engine exhaust nozzle temperature no. 5 Engine exhaust nozzle temperature no. 6 Engine exhaust nozzle temperature no. 7 Engine exhaust nozzle temperature no. 8

0 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87 70 - 87

rpm deg f deg f deg f deg f deg f deg f deg f deg f deg f deg f deg f deg f deg f deg f

TT7A TFUEL TOILIN TOILSC PBARO PS1 PS3 PGEAR MOP POILSC TORQ2 TORQ2S DELP VBGEA TORQ1 THETA THETAR DELTA

Tt1 Tt5

Tt7 Tf

Pam Psn Ps3 Prgb

Pam ∂P

TH RTH DEL

Engine exhaust nozzle temperature average Fuel temperature Oil temperature Scavenge Oil temperature Ambient Barometric Pressure Test cell static pressure Compressure discharge static pressure Reduction Gearbox Static Pressure Main Oil Pressure Scavenge Oil pressure Engine Torquemeter Pressure Engine Torquemeter Static Pressure Delta TORQ2 - TORQ2S Gearbox vibration Dyno torque THETA Ѵ THETA (AKAR THETA) DELTA (PBARO (inHg)/29.921)

70 - 87 70 - 87 70 - 87 70 - 87 13.3 - 13.5 same with pbaro 0 0 0 0 0 0 TORQ2 - TORQ2S 0 0 0.92 - 1.053 1.01 - 1.03 0.905 - 0.918

deg f deg f deg f deg f psia psia psig psig psig psig psig psig psig G's ft lbs

6

PT6A series engine testing IF ASSUMED THAT ENGINE TREATED AS OVERHAUL AND COMPRESSOR ROTOR HAVE BEEN BALANCING, THEN TEST PROCEDURE SEQUENCE IS:

START ENGINE MOTORING, STARTING & SHUTDOWN

RUN-IN PROCEDURE

1. 2. 3.

PRELIMINARY CHECK : OBTAIN NF/RTH = 33000 RPM PERFORM 2 FEATHERING OPERATION OIL PRESSURE CHECK

AGB VIBRATION SURVEY

RGB VIBRATION CHECK

ACCELERATION & BODIE CHECK

TT5 TRIM DETERMINATION

A 7

PT6A series engine testing IF ASSUMED THAT ENGINE TREATED AS OVERHAUL AND COMPRESSOR ROTOR HAVE BEEN BALANCING, THEN TEST PROCEDURE SEQUENCE IS:

A

ACCEPTANCE CHECK / PERFORMANCE

MINIMUM GOVERNOR CHECK

PROPELLER GOVERNOR MAXIMUM SPEED

UNDERSPEED FUEL GOVERNING CHECK

MAXIMUM NG ADJUSTMENT

MINIMUM FUEL FLOW CHECK

POST TEST RUN CHECK

PRESERVATION

FINISH 8

PT6A series engine testing ENGINE TEST OPERATING CONDITION LIMIT PARAMETE R

NG (rpm)

PT6A-21 38,100 (101.7%)

PT6A-27/28 38,100 (101.7%)

PT6A-25 38,100 (101.7%)

38,500 (102.75%) 34,200 (103.6%) 36,300 (110%)

38,500 (102.75%) 34,200 (102.9%) 36300 (109.2%)

38,500 (102.75%) 34,200 (103.6%) 36,300 (110%)

Start

1350

1440

1350

Steady State (trimmed)

1283

1380

1283

Steady State (untrimmed)

1325

1400

1325

Steady State

92

125

94

Acceleration*

94

127

94

Steady State Acceleration

NF (rpm)

Steady State Acceleration*

TT5 (deg F)

delP (inHg)

LIMIT

MAXIMUM OPERATING CONDITION

NOTE : Rundown time on the compressor from ground-idle must not be < 20 seconds *2 second time limit

SUPPLEMENTARY LIMITATION PARAMETER Fuel pressure @ engine inlet all time including transient Oil temperature for all running except transient Scavenge oil b ack pressure @ engine outlet Maximum permitted difference between individual inlet temp. indication

LIMIT 5 - 20 psig 140 - 160 deg F 20 - 50 psig

8:F

Maximum permitted difference between average Tt7 thermocouple reading between each exhaust nozzle assembly

60:F

Maximum permitted difference between thermocouple within a given nozzle

100:F

Maximum operating vibration limit

100 G's

Maximum acceptance vibration limit

70 G's

9


ENGINE MOTORING, STARTING & SHUT DOWN 

WET MOTORING RUN IF FIRE CONDITIONS OCCURS WITHIN ENGINE DURING MOTORING RUN , IMMEDIATELY CLOSE FUEL SHUTOFF VALVE AND CONTINUE MOTORING ENGINE ALLOW SUFFICIENT STARTER COOLING PERIOD BETWEEN MOTORING CYCLES AND ENGINE START; REFER TO STARTER MANUFACTURERS LIMITS AND RECOMMENDATIONS.



DRY MOTORING RUN This procedure is used to remove internally trapped fuel and fuel vapor, or if there is evidence of fire within the engine. Air passing through the engine serves to purge fuel/fuel vapor from the combustion section, power turbine and exhaust system.



ENGINE STARTING ALLOW SUFFICIENT STARTER COOLING PERIOD BETWEEN MOTORING CYCLES AND ENGINE START; REFER TO STARTER MANUFACTURERS LIMITS AND RECOMMENDATIONS. THE ENGINE MUST START AND REACH IDLE WITHIN 35 SECONDS OF INITIATION OF THE START. THE FIRST START OF THE DAY CAN SOMETIMES TAKE LONGER; THEREFORE, THE START TIME MUST BE CORRECTED TO COMPENSATE FOR LONG TIME TO LIGHT. FOR TTL GREATER THAN 3 SECONDS: TTI MODIFIED = TTI RECORDED - (TTL – 3 SECONDS). IF THIS REQUIREMENT IS NOT ACHIEVED, check the FCU pneumatic system for leaks. If no leaks are found, replace the

FCU.

IF Tt5 OBSERVED EXCEEDS 1440°F OR CONTINUOUS FLAME ISSUES FROM EXHAUST, SHUT OFF START CONTROL LEVER IMMEDIATELY. DO NOT ATTEMPT TO RELIGHT ON RUNDOWN; WAIT UNTIL THE ENGINE COMES TO REST, THEN IMPLEMENT A DRY MOTORING CYCLE TO COOL THE ENGINE 10


ENGINE MOTORING, STARTING & SHUT DOWN 

SHUT DOWN IF A FIRE OCCURS IN THE ENGINE AFTER SHUTDOWN, DO A DRY MOTORING RUN IMMEDIATELY

For normal shut down, allow engine to run at ground idle for at least one minute to stabilize at minimum running temperatures.

11


RUN-IN PROCEDURE NOTE : This procedure is to be done after scheduled or unscheduled overhaul/repair has been completed.

1)

Do a wet motoring run followed with a dry motoring run.

2)

Start the engine and run at ground-idle 19750 ± 500 rpm Ng (propeller testing) or rotate dynamometer controller to obtain 5000 rpm Nf or maximum available (dynamometer testing) for 5 minutes.

3)

Record Ng, Nf, Tt1, Tt5, del P, oil pressures and oil temperatures.

12


AGB VIBRATION SURVEY NOTE: 1. The vibration survey requirement applies only to engines being tested following overhaul or repair requiring balancing of the compressor rotor assembly. NOTE: 2. Do the vibration survey using the following procedures and the ACES Operator’s Manual. Personnel must be familiar with the Analyzer prior to performing these operations. CAUTION: DO NOT EXCEED ENGINE OPERATING LIMITS. ENGINE OPERATING LIMITS SUPERSEDE ANY INSTRUCTION IN ACES ANALYZER PROCEDURE.

ACCELERATION SURVEY Select ‘‘Acceleration Survey’’ from the menu on the analyzer.

1) 2)

Set power control lever to GROUND-IDLE.

3)

Set propeller control lever to 33000 rpm Nf.

4)

Ng Sweep: a)

Press ‘‘Enter’’ on the analyzer to start recording.

b)

Accelerate slowly at a rate of 5000 rpm/min from GROUND-IDLE to max available Ng without exceeding any operating limits. Reduce to GROUND-IDLE.

c)

Press ‘‘Enter’’ on the analyzer to stop recording.

13


AGB VIBRATION SURVEY SHUTDOWN SURVEY 1)

Select ‘‘shutdown Survey’’ from the menu on the analyzer.

2)

Press ‘‘Enter’’ on the ACES Analyzer to start recording. Shut down engine from idle.

3)

End vibration survey after engine reaches 0 rpm and a sync error appears on the ACES Analyzer; then press ‘‘Enter’’ on the ACES Analyzer to stop recording.

1ENg VIBRATION ACCEPTANCE LIMIT a.

From the plots produced above, ensure that 1ENg vibration level does not exceed the following limits: GROUND-IDLE to max Ng ; 0.5 cm/sec Shutdown from GROUND-IDLE to 5000 rpm Ng; 0.5 cm/sec

14


RGB VIBRATION CHECK NG SWEEP 1)

Set Nf to 33000 +100/-0 rpm.

2)

Carry out a slow acceleration (4,000 rpm/min.) from ground idle to maximum attainable Ng, do not exceed any operating limit.

3)

Carry out a slow deceleration (4,000 rpm/min.) from maximum attainable Ng to ground idle.

4)

Record Ng, Nf, torque and vibrations at the highest vibration peak from steps (2) and (3).

NF SWEEP 1)

Set Nf to 33000 +100/-0 rpm.

2)

Increase power to a torque of 80 ± 3 in. Hg

3)

Carry out a slow deceleration (4,000 rpm/min.) from 33000 +100/-0 rpm to 24,500 rpm. Engine torque must be kept at 80 ± 3 in. Hg during deceleration.

4)

Carry out a slow acceleration (4,000 rpm/min.) from 24,500 rpm to 33000 +100/-0 rpm. Engine torque must be kept at 80 ± 3 in. Hg during acceleration.

5)

Record Ng, Nf, torque and vibrations at the highest vibration peak from steps(3) and (4). 15


ACCELERATION & BODIE CHECK ACCELERATION CHECK 1)

If engine response is sluggish, or acceleration rate is too slow, check P3 and fuel system pneumatic control tubes and connectors for leakage or obstruction, before any fuel control adjustments are made

2)

Position power control lever maximum stop on console to limit torque to 86.3 in.Hg.(PT6A-21 engines) or 108.6 in.Hg. (PT6A-27/-28 engines) or maximum obtainable without exceeding engine operating limits. Lock stop on console.

3)

Rotate dynamometer controller to give 32000 rpm Nf (97% for PT6A-25, 96% for PT6A-27/28).

4)

Record Ng, Nf, Tt1 and δP.

5)

Decrease power control lever to flight-idle 23600 ± 100 rpm Ng.

6)

Slam accelerate from flight-idle to T.O. timed to 97.5% of take-off Ng. Slam decelerate to ground-idle (19750 ± 500).

NOTE: The time taken to move power control lever in checks (5) through (6) must not exceed 1.0 second, engine should respond smoothly during acceleration and deceleration.

16



NOTE: The time taken to move power control lever in checks (5) through (6) must not exceed 1.0 second, engine should respond smoothly during acceleration and deceleration.

7)

Acceleration time must fall within range specified

CAUTION: MAXIMUM ADJUSTMENT ON FCU ACCELERATION DOME TO MEET ACCELERATION TIME IS THREE CLICKS CLOCKWISE OR COUNTERCLOCKWISE.

8)

If necessary, adjust engine acceleration by rotating FCU acceleration dome one detent at a time, using minimum number to obtain satisfactory acceleration. Rotate dome clockwise to decrease (faster acceleration) and counterclockwise to increase (slower acceleration) acceleration time.

17



9)

For example, the inlet screen temp. (TT1) during the day is 80: F, then the acceleration time limits are : low limit = 2.42 + 0.35 = 2.77 seconds hi limit = 3.44 + 0.35 = 3.79 seconds

18


ACCELERATION & BODIE CHECK BODIE CHECK 1)

Rotate FCU acceleration dome three detents clockwise to increase fuel flow.

2)

Run engine for not less than one minute at maximum stop without exceeding operation limit (Ref. step (2) preceding) to achieve stabilization.

3)

Slam decelerate to 32000 Ng (85%), then without dwelling at lower speed, slam accelerate to maximum stop. Repeat to 26000 Ng (70%); again slam to maximum stop. Reduce Ng to GI.

4)

If engine is stall and surge free on completion of bodie checks, reset acceleration dome to original position (three detents counterclockwise).

5)

If engine stall or surge is experienced during checks, rotate acceleration dome one detent counterclockwise and repeat bodie check.

6)

If surge is still evident, check compressor bleed valve operation..

7)

If bleed valve is functioning correctly, the dome may be reset a further twodetents, a bodie check being implemented after each detent adjustment..

19


ACCELERATION & BODIE CHECK BODIE CHECK continued 8)

When surge is eliminated, reset dome three detents counter clockwise from surge-free setting.

9)

After satisfactory completion of bodie check following adjustment, recheck acceleration time (Ref. steps (5) and (6) ACCELERATION CHECK preceding).

10) Following acceptable acceleration and bodie checks, if scribe marks do not align, remove seal and lockwire on FCU acceleration dome. Holding adjusting screw with an Allen wrench, loosen adjuster locknut. Turn dome to re-align scribe marks, then tighten locknut, lockwire and seal. lockwire dome tab.

20


TT5 TRIM DETERMINATION 1)

Start engine, and advance power control and propeller control levers (propeller testing) or rotate dynamometer controller until engine is operating at observed power of 550 ± 10 SHPCEG (PT6A-21 engines) or 680 ± 10 SHPCEG (PT6A-27/-28 engines) or maximum power obtainable without exceeding engine operating limits and at an NFC equal to 33000 rpm but not to exceed 34200 rpm (NF observed).

2)

Run engine for 5 minutes at this power setting to obtain stabilization. Annotate log sheet; Tt5 Trim Determination and record set of readings. Nf, Ng, Pam or Baro, Psn or P1000, Ps3, Δp, SG, Tf, Tsg, Tt1, Tt5, Tt7

3)

Determine trim value from readings in step (2), preceding. Process Data with Program PWC83020.

4)

With results obtained in step (3) preceding, calculate trim to suppress TT5/TH to a value T5D/TH - 60° ± 10 F° (PT6A-21/-27/-28 engines) or T5D/TH - 65° ± 5 F° (PT6A-28 Piper engines only). Tt5 Trim Determination (example): TT5/TH = 1753°R T5D/TH = 1733°R T5D/TH - 60° = 1733 - 60 = 1673°R del T5/TH trim = 1753 – 1673 = 80°

5)

Trim value obtained in step (a) preceding is for a 59°F day. To trim engine, this value should be denormalized as follows:

del T5/TH x TH = del T5.

21


TT5 TRIM DETERMINATION continued 6)

Select appropriate class of trim harness (P/N 3013604 or P/N 3031417) (Ref. Table703).

7)

Install selected trim harness (Ref. Final Assembly), and record class in log sheet.

8)

Start engine and run at take-off power (Ref. step (1), preceding).

9)

After allowing for stabilization of readings, make sure that selected trim reduces Tt5 by the required value. If you are using program PWC83020, check the T5 trim check box and the output screen will state if the trim is good or not. Should it be necessary, install another class of trim and recheck.

22


TT5 TRIM DETERMINATION continued TABLE 703, Trim Harness Classification 3031417

± 5% @ 70°F Approx. Ohms

Approx. Range F°

3013604

Class 10

3.75 to 3.95

-208 to -200

-

Class 11

3.95 to 4.20

-200 to -190

-

Class 12

4.20 to 4.45

-190 to -180

-

Class 13

4.45 to 4.75

-180 to -171

-

Class 14

4.75 to 5.10

-171 to -161

-

Class 15

5.10 to 5.50

-161 to -151

-

Class 16

5.50 to 5.90

-151 to -142

-

Class 17

5.90 to 6.40

-142 to -132

-

Class 18

6.40 to 6.90

-132 to -123

-

Class 19

6.90 to 7.66

-123 to -114

-

Class 20

8

-114 to -104

-

Class 25

9

-104 to - 91

Class 1

Class 30

10.5

- 91 to - 80

Class 2

Class 35

12

- 80 to - 71

Class 3

Class 40

14

- 71 to - 61

Class 5

Class 45

16

- 61 to - 51

Class 7

Class 50

19

- 48 to - 45

Class 10

Class 55

24

- 40 to - 35

Class 20

Class 60

30

- 34 to - 28

Class 30

Class 65

43

- 25 to - 20

Class 40

Class 70

72

- 15 to - 10

Class 50

Class 75

110

- 9 to - 6

Class 60

23


TT5 TRIM DETERMINATION continued FLOW CHART OF TT5 TRIM DETERMINATION START

1. Run engine to maximum power obtainable, NFC = 33000 rpm, don't exceed operating limit. 2. Stabilize for 5 minutes. 3. Take fullset reading install trim harness TSG, SG, LHV, Ng, Nf, Pbaro, Psn, P3, Tt5, Torq1, delP, Wf,Tfuel, Tt1, Tt7

Input to and process with Program Drp PWC83020

1. Run engine to TAKEOFF or maximum power obtainable, NFC = 33000 rpm, don't exceed operating limit. 2. Make sure that selected trim reduces Tt5 by the required value.

SELESAI

TT5TH AND T5DTH

NOTE : TH = (Tt1+459.688)/518.688

example :

delT5TH = TT5TH - (T5DTH - 60)

delT5 = delT5TH x TH

TH = 1.05, TT5TH = 1753 R, T5DTH = 1733 R, delT5TH = 1753 - (1733 - 60) = 80, delT5 = 80 x 1.05 = 84, lookup table 703, p/n : 3031417 trim class = class 30, -91 to -80

delT5

LOOKUP TABLE 703

TRIM CLASS

24


TT5 TRIM DETERMINATION continued EXAMPLE OF TT5 TRIM DETERMINATION

The data from left column above, taken from fullset @ takeoff. The data will process with DRP program PWC83020. The output from program are : THETA = (ENGINE INLET TEMP + 459.688)/518.688 = (85.93 + 459.688)/518.688 = 1.05 T5D/THETA = 1723.8 deg R CORR.TT5 (TT5/THETA) = 1752.4 deg R

With refer to flow chart, then : (T5D/THETA ) - 60 = 1723.8 – 60 = 1663.8 DELTA TT5/ THETA TRIM = CORR.TT5 (TT5/THETA) – (T5D/THETA) – 60 = 1752.4 – 1663.8 = 88.6 DELTA TT5 DENORMALIZE = DELTA TT5/ THETA TRIM X THETA = 88.6 X 1.05 = 93.03 = 93 LOOKUP TO TABLE 703 → 93 → CLASS 25 OR CLASS 30

25


ACCEPTANCE CHECK (PERFORMANCE) Before we move deeply to Acceptance Check, better if we have a good understanding on several important parameter which were used for determine the result of acceptance check . The parameter which mentioned above are SHPCEG, NGC, WFC, SFC and TT5C.

26


ACCEPTANCE CHECK (PERFORMANCE) SHPCEG BLOCK DIAGRAM TORQ3 (static torq press)

psig

del P (torq2 - torq3 x 2.036) SHP (del P x NF / KONSTAN)

TORQ2 (torqmeter press)

psig

NF (power turbine speed)

rpm

KONSTAN PT6A-27 = 5272 PT6A-25 = 5183

SHPCEG (SHP / DELTA / sqroot THETA)

PBAR (ambient press)

psia

DELTA (pbar / standard press) standard press (14.696 psi) sq root THETA (theta ^ 0.5)

THETA (tt1 avg + 459.688) / 518.688

TT1 avg (engine inlet temp)

deg F

TT5C or TT5TH BLOCK DIAGRAM TT5 DEG R (tt5 + 459.688)

TT5 (interturbine temp)

deg F

THETA (tt1 avg + 459.688 / 518.688)

TT1 AVG (engine inlet temp)

deg F

TT5C or TT5TH (TT5 DEG R / THETA )

27


ACCEPTANCE CHECK (PERFORMANCE) WFC BLOCK DIAGRAM

CORR SPGRAV (spgrav-1.2875)/(ftsamp+1164)x(tfuel-ftsamf)+spgrav

FTSAMP (fuel sample temp)

deg F

SPGRAV (fuel spec. gravity)

psig

TFUEL (fuel temp)

deg F

WFGPM (fuel flow)

gpm

WFPPH (wfgpm x 499.68 x corr spgrav)

WFC (wfpph / DELTA x sqroot THETA)

PBAR (ambient press)

psia

DELTA (pbar / standard press) standard press (14.696 psi) sq root THETA (theta ^ 0.5)

THETA (tt1 avg + 459.688) / 518.688


deg F

SFCC BLOCK DIAGRAM SHPCEG (corr shp engine)

hp

WFC (corr WF)

pph

SFCC (shpceg / wfc)

28


ACCEPTANCE CHECK (PERFORMANCE) NGC BLOCK DIAGRAM sq root THETA (theta ^ 0.5)

THETA (tt1 avg + 459.688) / 518.688


deg F

NG (gas producer speed)

rpm

NGC (ng / sqroot THETA)

TT7C BLOCK DIAGRAM THETA (tt1 avg + 459.688) / 518.688


deg F

TT7 AVG (engine exhaust nozzle temp)

deg F

TT7AC (TT7A DEG R / THETA)

TT7A DEG R (tt7 avg + 459.688)

PS3C BLOCK DIAGRAM PBAR (ambient press)

psia

DELTA (pbar / standard press) PS3C (PS3 / DELTA )

standard press (14.696 psi) PS3 (compressor discharge press)

psig

29


ACCEPTANCE CHECK (PERFORMANCE) PROCEDURE CAUTION : DO NOT EXCEED ENGINE OPERATING LIMITS

1)

Run to following powers at Nf/RTH equal to 33000 rpm, but not to exceed 34200 rpm (observed).

2)

Record readings for each of the power setting points :

3)

PT6A-21 or PT6A -25 engines: :

4)

5)

a)

550 SHP/DELRTH or maximum power obtainable.

a)

495 SHP/DELRTH.

PT6A-27/28 engines: :

a)

680 SHP/DELRTH or maximum power obtainable.

a)

620 SHP/DELRTH.

From readings obtained in steps (3) or (4) preceding, process data with program PWC83020. Plot the best straight line across the normalized values of Wf, Tt5 and Ng against shp on engine performance graph. (Ref. Fig. 711). 30


ACCEPTANCE CHECK (PERFORMANCE) PROCEDURE

31


ACCEPTANCE CHECK (PERFORMANCE) ACCEPTANCE VALUE 1)

Enter curve at 550 shp (PT6A-21 engines) or 680 shp (PT6A-27/-28 engines) and record corresponding values for SFC, Tt5 and Ng for takeoff power in corrected engine performance block.

2)

Check parameters determined in step (1) against required parameters (Ref. Table 704).

32

PT6A series engine testing ACCEPTANCE CHECK (PERFORMANCE) ACCEPTANCE VALUE

33


ACCEPTANCE CHECK (PERFORMANCE) ACCEPTANCE VALUE

34



35



36



37



38



39



40



41


ACCEPTANCE CHECK (PERFORMANCE) ACCEPTANCE CHECK – performance calculation example

42


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46

PT6A Engine Testing

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