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WADC TECHNICAL NOTE 56-295

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KAMILTON-oTAKDARD MODEL JFC12 CONTROL METERING CHARACTERISTICS ,

Mr. J^ G./Barrett Power Plant Laboratory

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II 9 Jul® 05^

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Er.QJ9Ct No. 3031--(0142 -■<

Wright Air Development Center Air Research and Development Command

United States Air Force .Vri^-ht-Patterson Air Force Base, Ohio

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Wright Air Development Center Air Research and Development Conmand

united States Air Force WCLPG2/JGB/ml« Wright-Patterson Air Force Base, Ohio (Page 1 of 7 Pages)

Teohniftal Note Power Plant Laboratory WADC 5^-?95 Directorate of Laboratories 9 July 195b Project No. "jOH-lOl/;?

HAMILTON-STANDARD MODEL JFC12 CONTROL MKTERING CHARACTERISTICS

A. PURPOSE:

1. To obtain typical acceleration, deceleration and governing control churucteriatlcs of the Model JFC1? Fuel Control over a range of engine oper- ating conditions and fuel density.

B. FACTUAL DATA :

2. The Model JFC12 control is a hydromechanical design produced by Hamilton-Standard for the model J57 engine. This control has as inputs the high pressure compressor turbine assembly rotating speed (N~) , burner pres- sure (Pg), and power lever angular position. It controls fuel flow through by-pussing the excess output from n fixed displacement. Continuous hydro- mechanical computing establishes metering valve area. A constant metering head is held across the metering valve. Principle control provisions are described briefly as followsi

a. For engine acceleration a ratio of fuel flow rate to burner pressure (W£./Pg) Is held. Compressor inlet temperature trim (T2) reduces the ratio at certain conditions in order to skirt compressor surge.

b. The deceleration provision is likewise a ''f/Pg ratio except where this would yield a fuel flow less than fixed minimum flow which is obtained on a minLnum metering valve stop.

c. Speed governing is of the proportional type. Steady state Ng is controlled by the intersection of the control generated curve and the en- gine fuel flow requirement. Inlet temperature bias (Tp) lowers the control- led N2 as T2 is reduced (to prevent N^ from overapeed).

3. Hamilton- tandard Model JFC1?, Part No. 95^25, Serial No. 1572, was set-up in the Lngine Accessories Laboratory for this teat. The test was conducted on Meriam Test Stand Model No. D20399• The tests were conducted during the period of 3 - 10 May 195^. Two fuels were provided in order to have a range of specific gravity. These fuels were (a) MIL-F-7G2V. specific gravity 0.7^5 at OOT and (b) Jl5 with a specific gravity of O.783 at SOT.

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tt. The test results obtained are given in the attached curves. Significant notes on these curves are as follows;

a. Reference: Figure 1. A plot of the full throttle acceleration, governing and minimum flow with the two fuels at burner pressures of 5.0, 12.5 and 20.0 psia is shown. The curves represent typical very high altitude per- formance. The reduction of '^f/Pß to avoid compressor surge during acceleration is clearly shown.

b. Referencei Figure 2. A plot of idle throttle position metering for the conditions of overspeed, governing, and underspeed with the two fuels and range of burner pressures is given.

c. Reference: Figure j. The plot of full throttle metering at in- let temperatures (T2) of 72T and -S/^T is shown. The governor is seen to re-8et by 200 control shaft RFM with this range of temperatures. The control exhibits approximately 20 RPM hysteresis as noted in the Increasing vs. de- creasing run. The curve also shows the surge notch which progressively comes into effect as T2 is reduced.

d. Reference: Figure h. This curve illustrates the increase in fuel flow as burner pressure is increased. The full curve is piven for Pg of 150 psia and T2 of 72°?, a condition approximating ground level perform- ance.

The above curves may be used by interpolation to define specific control per- formance within the range of test conditions.

5. The fuel density effect on metering was determined to approximate the square root of the specific gravity ratio. Metered flow increased an average of 1.2^ for a specific gravity increase from O.765 to O.783.

C. CüNCLUSIONGi

6. Typical accelerating, decelerating and governing curves of the JFC12 control were determined covering a range of altitude conditions tFüj, power lever angle, inlet temperature and fuel density.

D. REGOmENDATIQNC;

7. None. Data merely submitted.

COORDINATION 1 ^ /,

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ENGINE ACCKTi-uRIEJ BRANCH

PREPARED BY«

-//A ;///U/.r / tV U&Jtf/d /JAMES G. BARRETT. /.'CLPG

9 July 1956 WADC TO 5b-295

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PUBLICATION REVIEW

This report has been reviewed and is approved..

FOR THE COMMANDERi

DISTRIBLTnON: IV Ä^ c> V^J

9 July 1956 WADC TN 56-295

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