CN108729956A - A kind of high temperature and pressure roturbo blade cooling system - Google Patents

Abstract

The invention belongs to field of fluid machinery, disclose a kind of high temperature and pressure roturbo blade cooling system, including refrigerating module, three parts of control module and circulating line module, refrigerating module includes mainly the components such as compressor, condenser, throttle valve and front evaporator and finisher；Control module includes the components such as shut-off valve, check valve, thermometer and pressure gauge；Circulating line module includes circulating pump, admission line, the components such as outlet pipe.High temperature and pressure roturbo is cooled down with hollow blade by increasing a cooling system, the service life of hollow blade can be extended, improves roturbo operational efficiency under high temperature and high pressure condition.

Description

Blade cooling system for high temperature and high pressure turbine pump

technical field

The invention belongs to the field of fluid machinery, and relates to a blade cooling system for a turbo pump, which is suitable for high-temperature and high-pressure environments.

Background technique

A turbine is a machine that converts the energy contained in a fluid medium into mechanical work, also known as a turbine. Turbines can be divided into water turbines (used as power sources for hydropower stations), steam turbines (used for thermal power plants, ship propulsion, etc.), gas turbines (used as propulsion power for jet aircraft, ship power, etc.) according to the fluid medium used. , as well as power plants, small power plants for peak loads, etc.) and air turbines (can only be used as small power), etc. Among them, the water turbine can be realized by the turbine pump, that is, the forward rotation is the water pump working condition, and the reverse rotation is the water turbine working condition.

At present, the efficiency of the turbopump disclosed in China is not very good under high temperature and high pressure conditions. One of the important factors is that the blades of the turbopump are seriously damaged under high temperature and high pressure conditions, which cannot make the turbopump safe and stable. run.

Patent application number 201610091924.6 discloses a method for measuring the temperature distribution of the pump cooling system. The equivalent physical model of the shielded nuclear main pump cooling system can be established to obtain the overall temperature distribution of the shielded nuclear main pump cooling system, which is convenient for the system Analysis, but did not propose an effective solution when the temperature is too high. Patent application number 201210288672.8 discloses a Roots vacuum pump cooling system, which overcomes the unsatisfactory cooling effect and poor sealing of the cooling system of the existing Roots vacuum pump, thereby reducing the overall performance and service life of the vacuum pump, but its applicability is not It is not wide and cannot be extended to turbo pumps under high temperature and high pressure conditions. Patent Application No. 201110181530.7 discloses an electromagnetic pump cooling system and its control method. Cooling oil is used to directly cool the electromagnetic pump coil, avoiding the possibility of air and water contacting liquid metal. At the same time, the cooling capacity is strong and the operating temperature of the coil can be guaranteed. , It also has a strong reference value for turbo pumps, but its disadvantage is that it is not ideal under high temperature and high pressure conditions. Patent application number 201710107374.7 discloses a hollow blade for a turbo pump, which can be used under high temperature and high pressure, and provides a solution to cooling the blade, but does not elaborate on the entire cooling system.

Contents of the invention

In view of the above defects, the present invention adopts a blade cooling system for high-temperature and high-pressure turbine pumps, which can effectively enhance the cooling effect on hollow blades, improve the efficiency of blades under high-temperature and high-pressure working conditions, and ensure that the turbine pump is used in various Can run stably under working conditions.

The cooling system of the present invention is mainly used for a high-temperature and high-pressure turbine pump with hollow blades.

Described hollow blade comprises main wing working surface, main wing back, wing tip and wing tail, and described wing tip, main wing working surface and main wing back, wing tail are connected successively, and between wing tip, main wing working surface and main wing back, wing tail A cavity is formed between them, and is divided into two parts, the front cavity and the rear cavity by the reinforcing ribs. The front cavity and the rear cavity are connected by a gas channel. The cooling gas inlet is set in the front cavity, and the cooling gas outlet is set in the rear cavity. The cooling gas enters the front cavity from the cooling gas inlet of the hollow blade, flows through the gas passage into the rear cavity, and finally flows out from the cooling gas outlet.

The cooling system includes three parts: a cooling module, a control module and a circulation pipeline module. The cooling module includes a compressor, a condenser, a throttle valve, a front evaporator and a rear evaporator; the control module includes a shut-off valve; the circulation pipeline module includes a circulation Pump, air intake pipe, air outlet pipe.

The circulation pump is connected to the cooling gas inlet of the hollow blade through the air inlet pipe, and the cooling gas outlet of the hollow blade is connected to the circulation pump through the air outlet pipe to form a circulation pipe; the inlet pipe is provided with a stop valve, and the outlet pipe is provided with a cooling module , the cooling module is close to the circulation pump.

The cooling module includes a front evaporator, a rear evaporator, a compressor, a condenser and a throttle valve connected in sequence, and the front evaporator and the rear evaporator are placed on the side of the outlet pipe.

The cooling gas in the circulation pipeline is pressurized and circulated by the circulation pump to cool the hollow blades, and the cooling module absorbs the heat of the cooling gas through the front evaporator and the rear evaporator to reduce its temperature.

The control module also includes a one-way valve, a thermometer and a pressure gauge, and the thermometer and pressure gauge are arranged on the intake pipe, between the circulating pump and the shut-off valve; the one-way valve is arranged on the air outlet pipe, between the hollow blade and the between cooling modules.

The diameter of the outlet pipe used for setting the evaporator in the cooling module is at least 1.5 times the diameter of other pipes.

There are no less than two air intake pipes leading into the hollow blades, and a shut-off valve is installed on each air intake pipe.

The beneficial effects of the present invention are:

The invention adds a cooling system to cool the hollow blades used in the high-temperature and high-pressure turbine pumps, thereby prolonging the service life of the hollow blades and improving the operating efficiency of the turbine pumps under high-temperature and high-pressure working conditions.

Description of drawings

Fig. 1 is a sectional view of a hollow blade;

Fig. 2 is a cross-sectional view of a hollow blade in the direction of A-A;

Figure 3 is a diagram of the cooling system.

Among them: 1. Cooling gas inlet, 2. Front cavity, 3. Gas channel, 4. Rear cavity, 5. Cooling gas outlet, 6. Wing tip, 7. Wing tail, 8. Rib, 9. Main wing working surface, 10. Back of main wing, 11. Circulation pump, 12. Thermometer, 13. Pressure gauge, 14. Stop valve, 15. Air intake pipe, 16. Check valve, 17. Air outlet pipe, 18. Front evaporator, 19. Rear Evaporator, 20. Compressor, 21. Condenser, 22. Throttle valve, 23. Cooling module, 24. Hollow blade.

Detailed ways

Below in conjunction with accompanying drawing and specific embodiment the present invention is further described:

As shown in accompanying drawings 1, 2 and 3, Fig. 1 is a sectional view of the hollow blade, Fig. 2 is a sectional view of the hollow blade in the A-A direction, and Fig. 3 is a diagram of the hollow blade cooling system of the high temperature and high pressure turbine pump.

The cooling system of the present invention is mainly used for a high-temperature and high-pressure turbine pump with hollow blades, which mainly includes a cooling module 23, a control module and a circulation pipeline module. The cooling module 23 mainly includes a compressor 20 and a condenser. 21. Throttle valve 22, front evaporator 18 and rear evaporator 19; control module includes stop valve 14, check valve 16, thermometer 12 and pressure gauge 13; circulation pipeline module includes circulation pump 11, air intake pipeline 15, air outlet pipeline17.

The circulation pump 11 is connected to the cooling gas inlet of the hollow blade through the air inlet pipe 15, and the cooling gas outlet of the hollow blade is connected to the circulation pump through the air outlet pipe 17 to form a circulation pipe; , a pressure gauge 13 and a shut-off valve 14; a one-way valve 16 and a cooling module 23 are arranged in sequence on the air outlet pipeline 17 from the hollow blade to the circulating pump. The cooling module 23 includes a front evaporator 18 , a rear evaporator 19 , a compressor 20 , a condenser 21 and a throttle valve 22 connected in sequence, and the front evaporator and the rear evaporator are placed on the side of the outlet pipe 17 .

As shown in Figures 1 and 2, the hollow blade is a special blade with an internal hollow structure, including the main wing working surface 9, the main wing back surface 10, the wing tip 6 and the wing tail 7, the wing tip 6, the main wing working surface 9 It is connected with the back of the main wing 10 and the tail of the wing in sequence, and forms a cavity between the wing tip 6, the working surface of the main wing 9, the back of the main wing 10, and the tail of the wing 7, and is divided into a front cavity 2 and a rear cavity 4 by the rib 8 The two parts, the front cavity 2 and the rear cavity 4 are connected by a gas channel 3, the cooling gas inlet 1 is set in the front cavity 2, and the cooling gas outlet is set in the rear cavity 4; the cooling gas is provided by the cooling gas inlet 1 of the hollow blade Enter the front chamber 2, flow through the gas channel 3 into the rear chamber 4, and finally flow out from the cooling gas outlet 5.

As shown in Figure 3, the cooling gas circulates in the circulation pipeline module, and the circulation pump 11 is used as the power source. The cooling gas passes through the intake pipeline 15, the cooling gas inlet 1, the front cavity 2 of the hollow blade, the gas passage 3, and the hollow blade. The rear cavity 4, the cooling gas outlet 5, the gas outlet pipe 17, and finally reach the circulation pump 11.

Further, the cooling gas inlet 1 and the cooling gas outlet 5 are respectively connected to the inlet pipe 15 and the outlet pipe 17 of the circulation pipe module.

The cooling gas in the circulation pipeline is pressurized and circulated by the circulation pump 11 to cool the hollow blades. In order to make the cooling effect better, the evaporator module should be divided into at least two parts, namely the front evaporator 18 and the rear evaporator 19 , the front evaporator 18 and the rear evaporator 19 are arranged on the side of the air outlet pipe 17 of the circulation pipe. Since the temperature of the cooling gas flowing out from the hollow blades is relatively high, the front evaporator 18 and the rear evaporator 19 should be arranged near the At the position of the circulation pump 11, it can dissipate heat naturally before passing through the front evaporator 18 and the rear evaporator 19; when the cooling gas passes through the front evaporator 18 and the rear evaporator 19, the The refrigerant absorbs the heat in the cooling gas, and the temperature of the cooling gas drops, which can achieve the purpose of cooling.

In order to enhance the cooling effect of the circulation pipe module, the pipe diameter of the outlet pipe 17 used to set the front evaporator 18 and the rear evaporator 19 should be at least 1.5 times the diameter of other pipes, so that the flow rate of the cooling gas becomes smaller, and the change of the pipe diameter will be As a result, the flow of cooling gas is unstable, and its heat transfer performance will become better.

The characteristic of the control module is that there are no less than two air intake pipes leading into the hollow blades, and a shut-off valve 14 is installed on each air intake pipe. Each of the cut-off valves 14 can be opened and closed separately to adjust the flow rate of the cooling gas. The thermometer 12 and the pressure gauge 13 are arranged on the inlet pipe 15 close to the circulating pump 11 as a reference for the switch of the cut-off valve 14, and the one-way valve 16 is arranged on the outlet pipe 17 to ensure the stable flow of cooling gas .

On each intake pipeline, one shut-off valve 14 can be set as required or multiple can be set in parallel.

As shown in FIG. 3 , the cooling module includes a compressor 20 , a condenser 21 , a throttle valve 22 , a front evaporator 18 and a rear evaporator 19 . The function of the compressor 20 is to compress the steam with lower pressure into steam with higher pressure, so that the volume of the steam is reduced and the pressure is increased. The compressor 20 sucks the lower-pressure steam from the evaporator, raises its pressure, and sends it to the condenser 21, where it is condensed into a liquid with a higher pressure, and after being throttled by the throttle valve 22, it becomes After the liquid with lower pressure is sent to the front evaporator 18 and the rear evaporator 19, it absorbs heat and evaporates in the front evaporator 18 and the rear evaporator to become a steam with a lower pressure, and then sends it to the inlet of the compressor 20, thus completing the entire refrigeration cycle.

The above is the specific description made with reference to the embodiments of the patent of the present invention, but the present invention is not limited to the above embodiments, and also includes other embodiments or modified examples within the scope of the concept of the present invention.

Claims (5)

1. A blade cooling system for a high-temperature and high-pressure turbine pump, said cooling system is used for a high-temperature and high-pressure turbine pump whose interior is a hollow blade of a hollow structure, and is characterized in that it includes a cooling module, a control module and a circulation pipeline module Three parts, the control module includes a shut-off valve; the circulation pipeline module includes a circulation pump, an air intake pipeline and an air outlet pipeline; The circulation pump (11) is connected to the cooling gas inlet of the hollow blade through the air inlet pipe (15), and the cooling gas outlet of the hollow blade is connected to the circulation pump (11) through the air outlet pipe (17) to form a circulation pipe; the air inlet pipe (15) A shut-off valve (14) is arranged on it, and a cooling module (23) is arranged on the outlet pipe (17), and the cooling module (23) is close to the circulation pump (11). 2. a kind of high temperature and high pressure turbine pump blade cooling system as claimed in claim 1, is characterized in that, described cooling module (23) comprises the front evaporator (18), back evaporator (19) that are connected successively, Compressor (20), condenser (21) and throttling valve (22), front evaporator (18) and rear evaporator (19) are placed on the outlet pipe (17) side. 3. A kind of blade cooling system for high temperature and high pressure turbine pumps as claimed in claim 1, is characterized in that, the pipe diameter of the position of the evaporator in the cooling module is at least the diameter of other pipes in the outlet pipe (17) 1.5 times. 4. a kind of blade cooling system for high temperature and high pressure turbine pump as claimed in claim 1, is characterized in that, described control module also comprises check valve (16), thermometer (12) and pressure gauge (13), so The thermometer (12) and the pressure gauge (13) are arranged on the air inlet pipe (15), between the circulation pump (11) and the shut-off valve (14); the one-way valve (16) is arranged on the outlet pipe (17) ), located between the hollow blade (24) and the cooling module (23). 5. A blade cooling system for a high-temperature, high-pressure turbine pump as claimed in claim 1, wherein there are no less than two air inlet pipes leading into the hollow blades, and a cut-off valve is installed on each air inlet pipe. valve.