RU2648197C1 - Gas-turbine engine testing method - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to the field of aircraft engine construction, namely to methods for testing aviation gas turbine engines (GTE). For a type of engine including an anti-icing system, preliminary tests are carried out in the selected operating mode, the parameters are measured when the anti-icing system is switched off and when the anti-icing system is switched on in the operating range of the rotor speed, calculating the correction factors to the measured parameters by the ratio of the values of the parameters measured with the de-icing system on, to the values of the parameters measured with the de-icing system switched off, the dependence of the correction factors on the measured parameters on the rotational speed of the rotors Ki=f(n), and when testing other engines in icing conditions with the de-icing system on, the measured values of the parameters are multiplied by the coefficients obtained.

EFFECT: method makes it possible to obtain reliable results when testing GTE under icing conditions with the anti-icing system on.

1 cl, 2 dwg, 2 tbl

Description

The invention relates to the field of aircraft engine manufacturing, namely to aircraft gas turbine engines (GTE) and methods for testing them.

A known method of testing aircraft gas turbine engines, which consists in measuring parameters according to engine operating conditions and bringing them to standard atmospheric conditions (Yu.A. Litvinov, V.O. Borovik. "Characteristics and operational properties of aircraft turbojet engines." M.: "Mechanical Engineering" 1979, pp. 136-137).

When implementing the known method, the influence of the anti-icing system on the engine parameters is not provided, which leads to incorrect determination of parameters at near-zero ambient temperatures when the anti-icing system is on and unreliable test results.

The objective of the invention is to enable the correct determination of engine parameters during tests with the anti-icing system turned on.

The technical result achieved by using the present invention is the ability to correctly determine engine parameters during testing under icing conditions with the anti-icing system on and to obtain reliable test results.

The specified technical result is achieved by the fact that in the known method of testing a gas turbine engine, which includes measuring the parameters according to the engine operating conditions and bringing them to standard atmospheric conditions, according to the present invention, for the type of engines including the anti-icing system, tests are preliminarily performed at the selected operating mode, the parameters are measured at off and when the anti-icing system is on in the operating range of rotor speed, calculate the correction factors for the measured steam meters by the ratio of the values of the parameters measured with the de-icing system turned on to the values of the parameters measured with the de-icing system turned off, the dependences of the correction factors on the measured parameters on the rotor speed Ki = f (n) are formed, and when testing other engines under icing conditions with With the included anti-icing system, the measured values of the parameters are multiplied by the obtained coefficients.

The proposed test method is implemented as follows.

Example

One prototype engine is tested on a test bench in the operating range of rotor speed and measure thrust and fuel consumption in the modes n _1пр = 70%, 75%, 80%, 85%, 90%, 95%, 100% when turned on and off anti-icing system.

Table 1 shows the thrust R and fuel consumption G _t measured at n _1pr = 70%, 75%, 80%, 85%, 90%, 95%, 100% with the de-icing system turned on and off:

The correction coefficients K _R and K _G are calculated taking into account the effect of the anti-icing system on the engine parameters, by the ratio of the parameter value measured with the anti-icing system turned on to the values of the parameter measured with the anti-icing system turned off (table 2):

According to the obtained values, the dependences of the correction coefficients K _R and K _G are constructed depending on the reduced rotor speeds n _1pr (Fig. 1 and Fig. 2).

When testing another prototype engine under icing conditions with the anti-icing system on, the thrust R _POS and fuel consumption G _{tPOS are measured} at a rotor speed of n _1pr = 90%.

Then, according to the obtained dependences, the coefficients K _R and K _G are determined and the obtained values of thrust and fuel consumption are multiplied by these coefficients:

R = R _PIC × K _R = 5834 × 1.0041 = 5858 kg;

G ₁ = G _{t POS} × K _G = 4656 × 0.9949 = 4632 kg / h.

The obtained coefficients are used to calculate engine parameters at different rotor speeds under icing conditions with the anti-icing system on.

The method allows to correctly determine the parameters of the engine during testing under icing conditions with the anti-icing system turned on and provides reliable test results.

Claims (1)

A method of testing a gas turbine engine, including measuring parameters according to engine operating conditions and bringing them to standard atmospheric conditions, characterized in that for the type of engines including an anti-icing system, tests are preliminarily performed at a selected operating mode, parameters are measured with the anti-icing system switched off and on operating range of rotor speed, calculate the correction factors to the measured parameters by the ratio of the values of the parameters measured with the anti-icing system turned on, the values of the parameters measured with the anti-icing system turned off form the dependences of the correction factors on the measured parameters on the rotor speed Ki = f (n), and when testing other engines under icing conditions with the anti-icing system turned on, the measured parameter values are multiplied on the obtained coefficients.

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