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used after approval by the certijkating authority.
7.1.4 Comction of emission indices
to reference conditions
Corrections shall be made to the measured engine emission
indices for all pollutants in all relevant engine operating
modes to account for deviations from the reference conditions
(ISA at sea level) of the actual test inlet air conditions of
temperature and pressure. The reference value for humidity
shall be 0.00634 kg waterkg dry air.
Thus, El corrected = K x EI measured,
where the generalized expression for K is:
T~rcf Temperature at the combustor inlet under ISA
sea level conditions for the engine tested (or the
reference engine if the data is to be corrected to
a reference engine). This temperature is the
temperature associated with each thrust level
specified for each mode.
F&f Fuelfair ratio in the combustor under ISA sea
level conditions for the engine tested (or the
reference engine if the data is to be comcted
to a reference engine).
a,b,c,d Specific constants which may vary for each
pollutant and each engine type.
The combustor inlet parameters shall preferably be
measured but may be calculated from ambient conditions by
appropriate formulas.
7.1.5 Using the recommended curve fitting technique
to relate emission indices to combustor inlet temperature
effectively eliminates the exp (ITBEf - T&) term from the
generalized equation and for most cases the (FARmf /FARs)
term may be considered unity. For the emissions indices of CO
and HC many testing facilities have determined that the
humidity term is sufficiently close to unity to be eliminated
from the expression and that the exponent of the (PBEf /PB)
term is close to unity.
EI(C0) corrected = El derived from
(PBIPhf) * EI(C0) v. TB curve
EI(HC) corrected = EI derived from
(PB lPBref) - EI(HC) v. TB curve
-24/11/05
NO. 5
Annex 16 - Environmental Protection Volume ZZ
EI(N0,) corrected = EI derived from
EI(NO,) (PBd / P ~ ) ~ .(~19 ( h - 0.00634 ( ) V. TB curve
If this recommended method for the CO and HC emissions
index correction does not provide a satisfactory correlation, an
alternative method using parameters derived from component
tests may be used.
Any other methods used for making corrections to CO, HC
and NO, emissions indices shall have the approval of the
certificating authority.
7.2 Control parameter functions
<Dp, Fm, d
The manufacturer shall also supply to the certificating
authority all of the necessary engine performance data to substantiate
these relationships and for ISA sea level ambient
conditions:
d) maximum rated thrust (F,); and
e) engine pressure ratio (x) at maximum rated thrust.
Note.- These are illustrated by Figure 5-3 d).
7.2.3 The estimation of EI for each pollutant at each of
the required engine mode settings, corrected to the reference
ambient conditions, shall comply with the following general
procedure:
7.2.1 Definitions a) at each mode ISA thrust condition F,, determine the
equivalent combustor inlet temperature (TB) (Figure
Dp The mass of any gaseous pollutant emined during the 5-3 c));
reference emissions landing and take-off cycle.
b) h mt he E qch aracteristic (Egure 5-3 a)), determine
F, The maximum thrust available for take-off under the EI, value corresponding to TB;
normal operating conditions at ISA sea level static
conditions, without the use of water injection, as C) from the W, jrg characteristics (Figure 5-3 b)).
approved by the applicable certificating authority. determine the Wfn value corresponding to TB;
The ratio of the mean total pressure at the last
compressor discharge plane of the compressor to the d) note the ISA maximum rated thrust and pressure ratio
mean total pressure at the compressor entry plane values. These are F, and n respectively (Figure 5-3 d));
when the engine is developing take-off thrust rating
at ISA sea level static conditions. e) calculate, for each pollutant Dp = C o3,J (Wfn) (t)
where:
7.2.2 The emission indices @I) for each pollutant,
corrected for pressure and humidity (as appropriate) to the t time in LTO mode (minutes)
reference ambient atmospheric conditions as indicated in 7.1.4
and if necessary to the reference engine, shall be obtained for
the required LTO engine operating mode settings (n) of idle,
Wh fuel mass flow rate (kglmin)
approach, climb-out and take-off, at each of the equivalent
corrected thrust conditions. A minimum of three test points C is the summation for the set of modes comprising the
shall be required to define the idle mode. The following reference LTO cycle.
　
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