CN204283626U - Fuel closed-loop control device in a kind of Study On Start-up Process For Gas Turbines - Google Patents

Abstract

The utility model easily causes overtemperature or suspension problem for solving fuel opened loop control in existing Study On Start-up Process For Gas Turbines, disclose fuel closed-loop control device in a kind of Study On Start-up Process For Gas Turbines, to be applicable in ground gas turbine, aeroengine and other starting process, in the high power plant of fuel control overflow, in Study On Start-up Process For Gas Turbines, add fuel mass flow gauge, gas compressor tachogenerator, exhaust end temperature transducer.Gas turbine is lighted a fire successfully, and gas turbine controller passes through fuel mass flow gauge, velocity transducer, temperature transducer, real-time measuring and adjustation fuel quantity, thus realizes the fuel closed loop control in Study On Start-up Process For Gas Turbines.

Description

Fuel closed-loop control device in a kind of Study On Start-up Process For Gas Turbines

Technical field

The utility model relates generally to fuel regulation device in a kind of Study On Start-up Process For Gas Turbines, specifically, in Study On Start-up Process For Gas Turbines, based on rotating speed of gas compressor or the device controlling fuel quantity based on delivery temperature.

Background technique

Require higher to fuel control accuracy in Study On Start-up Process For Gas Turbines, the timeliness adopting traditional opened loop control scheme to be difficult to ensure to start and reliability, in addition, owing to adopting mechanical-hydraulic structure during traditional starting controls, closed loop control is adopted to realize difficulty larger, therefore, starting process only adopts opened loop control, but along with the development of electron controls technology, starting process adopts closed loop control to possess corresponding hardware and technical specifications, simultaneously, in starting process, opened loop control easily causes starting overtemperature or suspension problem, reduce the reliability of starting, the utility model just proposes in this context.

Summary of the invention

Easily there is the phenomenon such as overtemperature or suspension for solving in Study On Start-up Process For Gas Turbines in the utility model, and the problem such as Open-loop start reliability is low, and then propose a kind of fuel control unit based on rotating speed of gas compressor or turbine exhaust gas temperature.

For solving the problems of the technologies described above, according to one side of the present utility model, providing fuel closed-loop control device in a kind of Study On Start-up Process For Gas Turbines, comprising fuel metering and control unit A and gas generator unit B, it is characterized in that:

--described fuel metering and control unit A comprise the fuel tank, filter, petrolift, pressure maintaining valve, the main fuel valve that are connected successively by fuel conduit, wherein,

Be communicated with by fuel conduit between described fuel delivery side of pump and the import of pressure maintaining valve, between the import of described petrolift and the import of pressure maintaining valve, be also provided with the fuel conduit of a band safety valve; Described main fuel valve is communicated with the fuel inlet of secondary fuel control valve with the firing chamber of gas turbine by main fuel control valve in parallel;

Described fuel metering and control unit A also comprise gas turbine controller, speed measuring device of gas turbine, frequency variator, fuel mass flow gauge, wherein, described combustion gas wheel speed measurement device, frequency variator and fuel mass flow gauge all communicate to connect with described gas turbine controller; Described frequency variator is electrically connected with the drive motor of described petrolift, for described petrolift provides driving electric power; Described fuel mass flow gauge is arranged on the fuel conduit between described pressure maintaining valve and main fuel valve or is arranged on the fuel conduit between described fuel tank and petrolift;

--described gas generator unit B comprises inlet end, gas compressor, firing chamber, turbine and exhaust end; Described exhaust end is arranged an exhaust end temperature transducer communicated to connect with described gas turbine controller; The outlet of a fuel conduit and described main fuel valve is also passed through in the fuel inlet of described firing chamber.

Preferably, described gas compressor is connected by rotating drive shaft with between turbine.

Preferably, described gas turbine controller regulates the natural fuel supply of firing chamber by described frequency variator.

Preferably, described gas turbine controller passes through speed measuring device of gas turbine, fuel mass flow gauge, temperature transducer, real-time measuring and adjustation fuel quantity, thus realizes the fuel closed loop control in Study On Start-up Process For Gas Turbines.

The utility model is by rotating speed of gas compressor or turbine exhaust gas temperature closed loop control starting process fuel quantity relative to the remarkable advantage of prior art, improves reliability, and can effectively control and reduce the phenomenon such as surge or suspension generation in starting process.

Accompanying drawing explanation

Fig. 1 is Study On Start-up Process For Gas Turbines fuel closed-loop control device

Fig. 2 is that Study On Start-up Process For Gas Turbines is based on empirical value fuel control logic flow chart

Fig. 3 is that Study On Start-up Process For Gas Turbines is based on engine mathematical model fuel control logic flow chart

Fig. 4 is based on gas turbine mathematical model turbine exhaust gas temperature calculation flow chart

Fig. 5 is based on gas turbine mathematical model rotating speed of gas compressor calculation flow chart

Embodiment

For making the purpose of this utility model, technological scheme and advantage clearly understand, to develop simultaneously embodiment referring to accompanying drawing, the utility model is further described.

Embodiment one

As shown in Figure 1, fuel control principle and flow process are as shown in Figure 2 for control gear Placement.As shown in Figure 1, the device realizing fuel closed loop control in Study On Start-up Process For Gas Turbines of the present utility model, comprises fuel metering and control unit A and gas generator unit B.

Described fuel metering and control unit A comprise the fuel tank 1, filter 10, petrolift 11, pressure maintaining valve 13, the main fuel valve 14 that are connected successively by fuel conduit, be communicated with by fuel conduit between the outlet of described petrolift 11 and the import of pressure maintaining valve 13, between the import of described petrolift 11 and the import of pressure maintaining valve 13, be also provided with the fuel conduit of a band safety valve 12; Described main fuel valve 14 is communicated with the fuel inlet of secondary fuel control valve 7 with the firing chamber 17 of gas turbine by main fuel control valve 6 in parallel.

Described fuel metering and control unit A also comprise gas turbine controller 4, speed measuring device of gas turbine 2, frequency variator 3, fuel mass flow gauge 5, wherein, described combustion gas wheel speed measurement device 2, frequency variator 3 and fuel mass flow gauge 5 all communicate to connect with described gas turbine controller 4; Described frequency variator 3 is electrically connected with the drive motor of described petrolift 11, for described petrolift 11 provides driving electric power; Described fuel mass flow gauge 5 is arranged on the fuel conduit between described pressure maintaining valve 13 and main fuel valve 14 or is arranged on the fuel conduit between described fuel tank 1 and petrolift 11.

Gas generator unit B comprises inlet end 15, gas compressor 16, firing chamber 17, turbine 18 and exhaust end 8; Described exhaust end 8 is arranged an exhaust end temperature transducer 9 communicated to connect with described gas turbine controller 4; The outlet of a fuel conduit and described main fuel valve 14 is also passed through in the fuel inlet of described firing chamber 17.

As shown in Figure 2, when carrying out fuel and controlling, fuel metering and control unit A and unit B work simultaneously, when described gas turbine is in starting process, control fuel duty according to based on rotating speed of gas compressor fuel control logic with based on delivery temperature fuel control logic:

SS1. based on rotating speed of gas compressor fuel control logic: the actual speed recording gas compressor under different conditions according to speed measuring device of gas turbine 2, with the rotating speed N of each conditions dictate _εcontrast, as measurement rotating speed and rotating speed N _εthe absolute value of difference when being not more than maximum error, increase fuel duty, as measurement rotating speed and rotating speed N _εwhen the absolute value of difference is greater than maximum error, be switched to based on delivery temperature fuel control logic;

SS2. based on delivery temperature fuel control logic: by turbine exhaust gas temperature under temperature sensor measurement different conditions, with the temperature T required by each state _εcontrast, as measuring tempeature and temperature T _εwhen the absolute value of difference is less than maximum error, increase speed, as measuring tempeature and temperature T _εthe absolute value of difference when being greater than maximum error, if occur surge or hang phenomenon, the then starting of stopping gas turbine, if do not occur surge or hang phenomenon, then reduce fuel duty, by delivery temperature and temperature T _εthe absolute value of difference be stabilized in after within maximum error and proceed to start.Rotating speed N under each state of gas turbine _εwith temperature T _εn is given as by empirical formula _ε-0and T _ε-0.

Embodiment two

As shown in Figure 1, fuel control principle and flow process are as shown in Figure 3 for control gear Placement.Wherein reduced temperature T _εdraw by Fig. 4 workflow management, to specific speed N _εdraw by Fig. 5 workflow management.

Rotating speed N under each state of gas turbine _εwith temperature T _εcalculated by gas turbine mathematical model simulation, its flow process is:

By intake temperature T ₁, compressor pressure ratio π _c, compressor efficiency η _cand the adiabatic index γ of air _acalculate compressor delivery temperature T ₂, $T_2=T_1[1+({{\mathrm{\π}}_C}^{\frac{{\mathrm{\γ}}_a-1}{{\mathrm{\γ}}_a}}-1)/{\mathrm{\η}}_C];$

According to gas energy equation (m in firing chamber ¹+ m ^f) C _pgt ³-m ¹c _pat ²=m ^fh ^fη _cc(in equation, m ₁and m _frepresent air mass flow and fuel flow rate respectively, C _pgand C _parepresent the specific heat at constant pressure of combustion gas and air respectively, h _frepresent fuel enthalpy, represent η _ccrepresent the efficiency of firing chamber) calculate outlet temperature T ₃, $T_3=\frac{m_f{h}_f{\mathrm{\η}}_{\mathrm{cc}}+m_1{C}_{\mathrm{pq}}{T}_2}{(m_1+m_f)C_{\mathrm{pg}}};$

Gas temperature raises, and interior energy increases, and reaches turbine place, the external output work of gas expansion, turbine output rate W _twith gas compressor consumed power W _cofficial post gas turbine rotary speed increase △ N, wherein, (in formula, J represents the rotary inertia of solid of rotation, and N represents gas turbine rotary speed), rotating speed reaches N _model, N _ε-model=N ₂+ Δ N, turbine exhaust end temperature is reduced to T simultaneously _model, (in formula, π _trepresent the expansion ratio of turbine, γ _grepresent the adiabatic index of combustion gas, η _trepresent the efficiency of turbine).

The foregoing is only preferred embodiment of the present utility model, not in order to limit the utility model, all within spirit of the present utility model and principle, any amendment made, equivalent replacement, improvement etc., all should be included within scope of the present utility model.

Claims (4)

1. a fuel closed-loop control device in Study On Start-up Process For Gas Turbines, described gas turbine comprises fuel metering and control unit A and gas generator unit B, it is characterized in that:

Described fuel metering and control unit A comprise the fuel tank (1), filter (10), petrolift (11), pressure maintaining valve (13), the main fuel valve (14) that are connected successively by fuel conduit, wherein,

Be communicated with by fuel conduit between the outlet of described petrolift (11) and the import of pressure maintaining valve (13), between the import of described petrolift (11) and the import of pressure maintaining valve (13), be also provided with the fuel conduit of a band safety valve (12); Described main fuel valve (14) is communicated with the fuel inlet of secondary fuel control valve (7) with the firing chamber (17) of gas turbine by main fuel control valve (6) in parallel;

Described fuel metering and control unit A also comprise gas turbine controller (4), speed measuring device of gas turbine (2), frequency variator (3), fuel mass flow gauge (5), wherein, described combustion gas wheel speed measurement device (2), frequency variator (3) and fuel mass flow gauge (5) all communicate to connect with described gas turbine controller (4); Described frequency variator (3) is electrically connected with the drive motor of described petrolift (11), for described petrolift (11) provides driving electric power; Described fuel mass flow gauge (5) is arranged on the fuel conduit between described pressure maintaining valve (13) and main fuel valve (14) or is arranged on the fuel conduit between described fuel tank (1) and petrolift (11);

--described gas generator unit B comprises inlet end (15), gas compressor (16), firing chamber (17), turbine (18) and exhaust end (8); Described exhaust end (8) is arranged an exhaust end temperature transducer (9) communicated to connect with described gas turbine controller (4); The outlet of a fuel conduit and described main fuel valve (14) is also passed through in the fuel inlet of described firing chamber (17).

2. control gear according to claim 1, is characterized in that, is connected between described gas compressor (16) with turbine (18) by rotating drive shaft.

3. control gear according to claim 1, is characterized in that, described gas turbine controller (4) regulates the natural fuel supply of firing chamber by described frequency variator (3).

4. control gear according to claim 1, it is characterized in that, described gas turbine controller (4) is by speed measuring device of gas turbine (2), fuel mass flow gauge (5), temperature transducer (9), real-time measuring and adjustation fuel quantity, thus realize the fuel closed loop control in Study On Start-up Process For Gas Turbines.