KR20170121437A - Bypass door and anti-ice control method for marine gas turbine air intake device - Google Patents

Abstract

The present invention relates to a bypass door and an anti-freeze control method of a gas turbine air intake device for a ship, which prevent damage to a gas turbine due to interruption of air supply, comprising: a step of controlling a hot air generating portion at a front end of a filter by setting a reference temperature before filtering and comparing the temperature before filtering with the reference temperature; a step of setting a reference differential pressure with a flux before filtering; a step of setting a filter contamination alerting reference value by using a filter contamination alerting constant value according to the reference differential pressure; a step of setting a bypass door opening reference value by using a bypass door opening constant value according to the reference differential pressure; and a step of controlling the bypass door by determining whether or not the differential pressure detected via the front end and a rear end of the filter are larger than the filter contamination alerting reference value and the bypass door opening reference value.

Description

TECHNICAL FIELD [0001] The present invention relates to a bypass door and an anti-icing control method for a gas turbine intake apparatus for a ship,

[0001] The present invention relates to a bypass door for a gas turbine intake apparatus for a ship, and more particularly to a bypass door for preventing a damage to a gas turbine caused by interruption of air supply and inflow of cold air, And a method of controlling icing prevention.

Gas Turbine For the intake system of the ship, a filter system combining a separator and a filter is applied to supply clean air from which foreign substances and moisture are removed from the air.

In this case, when the combustion air sucked into the gas turbine is taken in the air, the filter removes foreign matter such as dust and dust contained in the air, cleanly purifies the gas, and then supplies the cleaned air to the gas turbine. , The filter is contaminated by consumable parts that require periodic cleaning and replacement, resulting in deterioration of gas turbine efficiency and damage to the gas turbine.

Thus, in case of an emergency in which the suction of air such as the clogging of the filter is obstructed due to the infiltration of excessive salt water by various pollutants or waves, the gas turbine is damaged and the operation of the ship becomes impossible. Therefore, It is necessary to replace the filter at an appropriate time. However, since it is not known clearly, the air supply to the gas turbine may not be smoothly performed.

Recently, in order to solve such a problem, a bypass door which bypasses the air without passing the filter and minimizes the damage of the engine is applied to the gas turbine intake apparatus for marine use.

However, in the case of the bypass door that bypasses such air, the user arbitrarily opens the door to open or observe the portion of the filter contamination periodically by the user to determine the replacement time of the filter.

In addition, when the ship is traveling in a cold region, the moisture particles in the air are frozen to form ice granules, and the ice granules continuously flow into the turbine, causing repetitive impact on the turbo engine blades, causing damage to the engine.

Accordingly, there is a need for an apparatus that minimizes damage to the turbo-engine of a variety of environmentally and structurally-occurring gas turbine devices.

Korean Registered Patent No. 0304596 (Registered on July 23, 2001, Air Filter for Intake Purification of Gas Turbine and Method for Manufacturing the Same) Korean Registered Patent No. 1399950 (Registered on May 31, 2014., Structure for preventing freezing of ballast tanks using insulation)

The present invention is to provide a bypass door and an anti-icing control method of a gas turbine intake apparatus for a ship, which can open a bypass door by fluidly applying different standards according to a flow rate of intake air flowing into an intake apparatus.

The present invention also provides a by-pass door and a method for controlling anti-freezing of a gas turbine intake apparatus for a ship, which uses a differential pressure before and after a filter to indicate a time for replacing an appropriate filter.

The present invention also provides a bypass door and an anti-icing control method for a marine gas turbine intake system that prevents freezing of ice particles into a turbine.

The technical objects to be achieved by the present invention are not limited to the above-mentioned technical problems.

In order to accomplish the above object, there is provided a bypass door and an anti-frost control method for a ship gas turbine intake system, comprising: setting a reference temperature before a filter; comparing a reference temperature with a temperature before the filter; Hot air) generating unit; Setting a reference differential pressure at a flow rate before the filter; Setting a filter pollution alarm reference value to a filter pollution alarm constant value according to the reference differential pressure; Setting a bypass door opening reference value to a bypass door opening constant value according to the reference differential pressure; And controlling the bypass door by determining whether the differential pressure detected through the front end and the rear end of the filter is larger than the filter pollution alarm reference value and the bypass door opening reference value, and if the differential pressure is smaller than the filter pollution alarm reference value, The pollution alarm elapsing time, and the bypass door opening elapse time.

And opening the bypass door when the differential pressure reaches or exceeds the bypass door opening reference time while the differential pressure is greater than the bypass door opening reference value.

If the elapsed time based on the time point at which the differential pressure is equal to or larger than the filter contamination alarm reference value reaches or exceeds the filter contamination alarm reference time, if the differential pressure is greater than the filter contamination alarm reference value and is not larger than the bypass door opening reference value, And generating a pollution alarm signal.

The filter contamination alarm constant value and the bypass door open constant value are variable according to the flow rate of the intake air sucked into the intake apparatus.

As described above,

The present invention has the effect of preventing damage of the turbine by preventing the ice particles generated due to the external low temperature from flowing into the turbine.

According to the present invention, it is possible to determine an appropriate filter replacement time regardless of the size of the intake apparatus through the differential pressure between the front and rear ends of the filter, which varies depending on the driving environment of the engine. So that the air can be supplied to the gas turbine by bypassing the filter in a secondary way, thereby enhancing the stability of the gas turbine engine.

In addition, the present invention has the effect of reducing an erroneous operation due to an instantaneous pressure rise or a change in conditions, thereby reducing unnecessary labor input and maintenance time.

1 is a structural view illustrating a gas turbine intake apparatus for marine vessels according to an embodiment of the present invention.
2 is a flowchart illustrating a bypass door and a method of controlling icing prevention in a gas turbine intake system for a ship according to an embodiment of the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In the drawings, the same components are denoted by the same reference symbols whenever possible. In the following description, well-known functions or constructions are not described in detail since they would obscure the invention in unnecessary detail.

FIG. 1 is a schematic view of a gas turbine intake apparatus for a ship according to an embodiment of the present invention. FIG. 1 is a schematic view of a gas turbine intake apparatus for a ship according to an embodiment of the present invention. Referring to FIG. 1, a gas turbine intake apparatus for a ship includes a filter 110, a hot air generating unit 120, a flow velocity measuring unit 130, A control unit 150, an alarm unit 160, and a bypass door 170.

The filter 110 removes foreign substances such as dust and dust contained in the air and purifies the air when it is taken into the atmosphere, and then supplies the cleaned air to the gas turbine.

At this time, the filter 110 is preferably positioned between the separators 111 and 112.

The hot air generating unit 120 is positioned at the front end of the filter 110 and receives a signal from the controller 150 through a signal measured from the temperature sensor unit 121 which is located before the hot air generating unit 120, .

The distance between the temperature sensor unit 121 and the hot air generator 120 is preferably such that the temperature changed by the hot air generator 120 is not affected by the temperature sensor unit 121.

If the temperature sensor 121 detects a change in temperature due to hot air in the temperature sensor unit 121 due to a distance between the temperature sensor 121 and the hot air generator 120, I can not do it.

The hot air generating unit 120 transmits the temperature measured by the temperature sensor unit 121 to the controller 150 so that the controller 150 compares the reference temperature with the inflow temperature, Or not.

The flow rate measuring unit 130 measures the flow rate of the air entering through the filter 110. In the embodiment of the present invention, the flow rate measuring unit 130 is provided before the filter 110 and measures the flow rate without passing through the filter 110. That is, it is desirable to measure the actual flow rate not canceled.

The differential pressure sensor unit 140 is positioned at the front end and the rear end of the filter 110, and measures a differential pressure of air entering through the filter 110.

The controller 150 notifies the replacement time of the filter 110 through the alarm unit 160 by using the flow rate and the differential pressure detected through the flow rate measuring unit 130 and the differential pressure sensor unit 140, And controls the bypass door 170 to open so as to bypass the filter 110 and supply air to the gas turbine to maintain the air supplied to the gas turbine when clogging occurs.

In other words, the alarm unit 160 can be displayed externally, regardless of whether it is a visual or an auditory display, and is not limited to an auditory display.

The bypass door 170 bypasses the filter 110 and bypasses the filter 110 to supply air to the gas turbine. The bypass door 170 is supplied with external air through the bypass door 170 only by the suction force of the gas turbine engine, so that it is not necessary to provide a means for supplying the separate air.

A method of controlling (170) the bypass door of the gas turbine intake apparatus for a ship will be described in detail as follows.

2 is a flow chart showing a marine gas bypass door and the freezing prevention control of the turbine intake apparatus according to an embodiment of the present invention, filter 110 set the previous reference temperature (T _ref) and the reference temperature (T _ref (T _in ) before the filter 110 and controls the hot air generator at the front of the filter (S 110).

If the temperature before the filter is lower than the reference temperature, the hot air generating unit 120 is operated to generate hot air to raise the temperature before the filter. And the hot air generation is not stopped or operated if the temperature before the filter is higher than the reference temperature.

At this time, it is preferable that the temperature sensor unit 121 for measuring the temperature before the filter and the hot air generating unit 120 are spaced apart from each other.

This is because, if the temperature sensor unit 121 and the hot air generator 120 are provided at a close position, the temperature measured by the temperature sensor unit 121 may be influenced.

By doing so, the temperature of the air passing through the filter 110 and flowing into the turbine is increased to prevent freezing of the ice particles.

Next, the reference differential pressure ΔP _normal is set at the flow rate before the filter 110 (S120). At this time, the flow velocity v before the filter 110 may be calculated in the flow velocity measurement unit 130, and the flow velocity measurement unit 130 may be a pitot tube.

Further, the flow velocity v can be obtained by the following equation (1).

는 유체의 밀도, △P₁은 필터 전단의 차압을 나타낸다. At this time,

Represents the density of the fluid, and [Delta] P ₁ represents the differential pressure across the filter.

Here, the differential pressure (ΔP ₁ ) at the front end of the filter means the differential pressure between the voltage and the static pressure of the pitot tube, which is the flow rate measuring unit provided at the front end of the filter.

)은 엔진의 환경 및 흡기장치의 규모에 따라서도 가변되므로 필터(110) 이전에 설치되어 상쇄되지 않은 유속이 측정되는 것이 바람직하다. Flow rate

Is variable according to the environment of the engine and the size of the intake apparatus, it is preferable that the flow rate which is installed before the filter 110 and is not canceled is measured.

)를 이용하여 기준차압(△P_normal)을 구하여 설정할 수 있다. The flow velocity thus calculated (

) Can be used to determine and set the reference differential pressure (ΔP _normal ).

Then, the filter pollution alarm reference value THF _{, D} is set to the filter pollution alarm constant value DELTA _{PF, D} according to the reference differential pressure DELTA _Pnormal at step S130.

At this time, since the filter contamination alarm signal may lose the function of the filter 110 as the differential pressure ΔP _{2 at} the front end and the rear end of the filter 110 increases due to dust and dust accumulated in the filter 110, So that the filter 110 can be replaced.

Here, the pressure difference (△ P ₂₎ is measured by differential pressure sensor 140, filter contamination alarm is output by the alarm unit 160.

Next, the setting of the reference pressure difference (△ P _normal) bypass the door opening constant value (△ P _open) to bypass the door opening reference value (TH _open) according to a (S140).

At this time, the filter contamination alarm constant value (? P _{F, D} ) and the bypass door open constant value (? P _open ) can be varied according to the flow rate of the intake air sucked into the intake apparatus, It can be easily applied in a fluid manner depending on the environment.

Finally, larger than the pressure difference (△ P _2), the filter contamination alarm reference value (TH _{F, D)} larger (S150), the bypass door opens the reference value (TH _open) is detected by the front and rear ends of the filter 110 ( S160) and controls the bypass door (170).

The pressure difference (△ P ₂₎ the filter contamination alarm reference value is smaller than _{(TH F, D) (S150} ), filter contamination alarm elapsed time (T _{D, i)} and the bypass door opens the elapsed time (T _{o, i)} 0 " (S151), and each elapsed time is counted to zero.

Then, the pressure difference (△ P ₂₎ by increasing the filter contamination alarm reference value (TH _{F, D)} larger (S150), is smaller than the bypass door opening reference value (S160) filter contamination alarm elapsed time (T _{d, i)} (S171), the filter contamination alarm reference time repeatedly until equal to (T _{D, delay)} or long pressure difference (△ P ₂₎ is measured.

In addition, the pressure difference (△ P ₂₎ the filter contamination alarm reference value (TH _{F, D),} if larger (S150), larger than the bypass door opening reference value (TH _open) (S160), the pressure difference (△ P ₂₎ is The filter pollution alarm elapsed time (T _{D, delay} ) is added to the filter pollution alarm reference time (T _{D, delay} ) by increasing the elapsed time based on a time point equal to or greater than the filter pollution alarm reference value (TH _{F, D} ) If it is reached or exceeded (S181), a filter contamination alarm signal is generated through the alarm unit 160 (S191).

If the pressure difference ΔP ₂ is greater than the bypass door opening reference value TH _open , the elapsed time is increased (S 172). If the bypass door opening elapsed time T _{o, delay} is greater than the bypass door opening reference time T _o, repeated until equal to the _delay) or long by measuring the pressure difference (△ P _2), and the pressure difference (△ P ₂₎ the by-pass the door opening reference value (TH _open) than the bypass door opening reference time as a large state (T _{o, delay} ) is reached or exceeded (S182), the bypass door 170 is opened (S192).

Since the embodiment of the present invention is based on a method of controlling the opening of the bypass door 170, the structural configuration according to how to open the bypass door 170 is devoid of the gist of the present invention, do.

According to the present invention as described above, the present invention has the effect of preventing damage to the turbine by preventing the ice particles generated due to external low temperature from flowing into the turbine.

Further, according to the present invention, it is possible to determine the replacement timing of a proper filter regardless of the size of the intake apparatus through the differential pressure between the front and rear ends of the filter, which varies depending on the driving environment of the engine. So that the air can be supplied to the gas turbine by bypassing the filter in a secondary way, thereby enhancing the stability of the gas turbine engine.

In addition, the present invention has the effect of reducing an erroneous operation due to an instantaneous pressure rise or a change in conditions, thereby reducing unnecessary labor input and maintenance time.

The bypass door and the anti-icing control method of the gas turbine intake apparatus for night time are not limited to the configuration and the operation of the embodiments described above. The embodiments may be configured so that all or some of the embodiments may be selectively combined so that various modifications may be made.

110: filters 111 and 112:
120: hot air generating unit 121: temperature sensor unit
130: flow velocity measuring unit 140: differential pressure sensor unit
150: control unit 160:
170: Bypass door

Claims (3)

A method for controlling a gas turbine intake system for a ship,
Setting the reference temperature before the filter, comparing the reference temperature with the temperature before the filter, and controlling the hot air generator at the front of the filter;
Setting a reference differential pressure at a flow rate before the filter;
Setting a filter pollution alarm reference value to a filter pollution alarm constant value according to the reference differential pressure;
Setting a bypass door opening reference value to a bypass door opening constant value according to the reference differential pressure; And
Controlling the bypass door by comparing the differential pressure detected through the front end and the rear end of the filter with the filter pollution alarm reference value and the bypass door opening reference value,
Further comprising the step of initializing the filter contamination alarm elapsed time and bypass door opening elapsed time if the differential pressure is smaller than the filter contamination alarm reference value.
The method according to claim 1,
And opening the bypass door when the differential pressure reaches or exceeds the bypass door opening reference time while the differential pressure is greater than the bypass door opening reference value. Prevention control method.
The method according to claim 1,
Wherein the filter contamination alarm constant value and the bypass door open constant value are varied according to the flow rate of the intake air sucked into the intake apparatus.

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