RU2773995C1 - Gas pumping unit - Google Patents

Abstract

FIELD: mechanical engineering.

SUBSTANCE: invention relates to gas pumping units, GPU, with high-temperature gas turbine engines as drives. The expected result was achieved in a gas pumping unit containing a gas turbine engine, an inlet device, a compressor, an annular combustion chamber with a heat pipe having an external heat wall and fuel-air nozzles on the nozzle plate connected through a fuel collector to the main fuel line, a turbine, a free turbine and an exhaust device, a synthesis gas system that contains a second a gas extraction system and an ejector line with an ejector mixer, to which the outputs of the second gas extraction system and an ejector line are connected, a preheating heat exchanger installed in the exhaust device is connected to the inlet from the ejector mixer, and a final heating heat exchanger with a catalyst is connected to the outlet of the ejector mixer through the second collector, characterized in that the ejector line is made in the form of a fuel ejector line, the final heating heat exchanger is installed inside the heat pipe on its outer heat wall and equipped with synthesis gas nozzles, and the catalyst is installed in the fuel channel of this heat exchanger.

EFFECT: task of the invention is increasing the efficiency of the unit.

5 cl, 8 dwg

Description

The invention relates to gas pumping units - GPA with high-temperature gas turbine engines as drives.

Known gas pumping unit, using one of the most effective methods to improve the efficiency of the combustion process and improve environmental performance, it is a method of adding to the hydrocarbon fuel a mixture of hydrogen and carbon monoxide, which can be obtained by reforming natural gas in the catalytic reactor of the synthesis gas generator (Tsybizov Yu .I., Eliseev Yu.S., Fedorchenko D.G. "The use of synthesis gas to ensure the environmental safety of gas turbines", Aircraft engines of the XXI century, Moscow, TsIAM. P. 461-462. 2015).

Disadvantages difficulties with heating the feedstock in the catalytic reactor above 600°C.

Known gas pumping unit according to the RF patent for the invention No. 2708957, IPC F02C 3/00, publ. 12/12/2019

This GPU contains a gas turbine engine, a fuel system and a synthesis gas system, which contains a second gas extraction system and an air extraction system due to the compressor, an ejector-mixer, to which the outlets of the second gas extraction system and the air extraction system are connected to the outlet of the ejector - the mixer is connected to a successor pre-heating heat exchanger installed in the exhaust device and a final heating heat exchanger installed on the chamber body and a catalyst.

Known gas pumping unit according to the application of the Russian Federation for the invention No. 2020116636, IPC F02C 3/00, prior. May 12, 2020, prototype.

This gas compressor unit contains a gas turbine engine with a compressor, a combustion chamber and a turbine, a free turbine and a blower compressor, a fuel system and a synthesis gas system, which contains a second gas extraction system and an air extraction system due to the compressor, an ejector-mixer, to which are attached the outlets of the second gas sampling system and the air sampling system, a successor pre-heating heat exchanger installed in the exhaust device and a final heating heat exchanger installed on the chamber body and a catalyst are connected to the outlet of the ejector-mixer, while the catalyst is installed inside the auxiliary fuel manifold, which is made inside the nozzle plate or on it and additional channels communicated with the air channels of the nozzle plate.

Disadvantage: low efficiency of the unit due to the large dimensions of the heat exchangers and low efficiency of the active radicals of the synthesis gas due to the significant time of passage of the synthesis gas from the heat exchanger to the synthesis gas nozzles. The lifetime of radicals and ions is a few nanoseconds,

The task of creating the invention is to increase the efficiency of the unit.

Technical result achieved: increasing the efficiency of the unit.

The solution to this problem was achieved in a gas-pumping unit containing a gas turbine engine, an inlet device, a compressor, an annular combustion chamber with a flame tube having an external flame wall and fuel-air nozzles on the nozzle plate connected through a fuel manifold to the main fuel line, a turbine, a free turbine and an exhaust device, a synthesis gas system, which contains a second gas extraction system and an ejector line with an ejector-mixer, to which the outlets of the second gas extraction system and an ejector line are connected, a preheating heat exchanger installed in the exhaust device is connected to the inlet from the ejector-mixer, and a final heating heat exchanger with a catalyst is connected to the outlet of the ejector-mixer through the second manifold, characterized in that the ejector line is made in the form of a fuel ejector line, the final heating heat exchanger is installed inside the flame tube on its outer flame tube. tank and is equipped with synthesis gas nozzles, and the catalyst is installed in the fuel channel of this heat exchanger.

The final heating heat exchanger may have ribs on the inner wall.

The ribs can be made in the form of longitudinal plates.

The ribs can be made in the form of cylinders.

The ribs can be made in the form of cones.

The essence of the invention is illustrated in Fig. 1…8, where:

in fig. 1 shows a schematic diagram of a gas pumping unit,

in fig. 2 shows the combustion chamber and fuel supply system,

in fig. 3 shows the final heat exchanger,

in fig. 4 shows a gas-air nozzle,

in fig. 5 shows a section A-A of a gas-air nozzle,

in fig. 6 shows the final heating heat exchanger 1 option,

in fig. 7 shows the final heating heat exchanger 2 option,

in fig. 8 shows the final heating heat exchanger 3rd option.

The list of features accepted in the description:

gas turbine engine - 1,

input device - 2,

exhaust device - 3,

free turbine - 4,

building - 5,

nozzle apparatus - 6,

impeller - 7,

working blades - 8.

shaft - 9,

blowing compressor - 10,

entrance building - 11,

output building - 12,

centrifugal impeller - 13.

inlet gas pipe - 14,

outlet gas pipe - 15,

air path - 16,

air intake - 17,

compressor - 18,

cavity - 19,

annular combustion chamber - 20,

turbine - 21,

gas path - 22,

guide apparatus - 23,

impeller - 24,

nozzle apparatus - 25,

impeller - 26,

flame tube - 27,

nozzle plate - 28,

gas-air nozzles - 29,

fuel manifold - 30,

shaft - 31,

the first support - 32,

second support - 33,

main fuel line - 34,

preheating heat exchanger - 35,

flow regulator - 36,

the second gas line - 37,

second valve - 38,

second collector - 39,

fuel ejector line - 40,

ejector-mixer - 41,

ejector valve - 42,

final heating heat exchanger - 43,

external flame tube - 44,

synthesis gas nozzle - 45,

heat exchanger fuel channel - 46,

outer annular wall - 47,

inner annular wall - 48,

ribs - 49,

catalyst - 50,

cylinder - 51,

cone - 52,

shank - 53,

building - 54,

outlet - 55,

guide vanes - 56,

inclined channels - 57,

ejector gearbox - 58,

ejector nozzle - 59.

The proposed gas pumping unit - GPA of increased efficiency is designed for pumping natural gas. GPA (Fig. 1) contains a gas turbine engine 1, an inlet device 2, an exhaust device 3, a free turbine 4, which in turn contains a housing 5, a nozzle apparatus 6 and an impeller 7 with rotor blades 8. The impeller 7 is connected by a shaft 9 to the injection compressor 10, containing an inlet casing 11, an outlet casing 12 and a centrifugal impeller 13. An inlet pipe 14 is connected to the inlet casing 11, and an outlet gas pipe 15 is connected to the outlet casing 12 (means for cleaning and cooling natural gas in Figs. 1 ... shown).

The gas turbine engine 1 contains an air path 16 containing, in turn, an air intake 17, a compressor 18 and a cavity 19 behind the compressor 18 and in front of the annular combustion chamber 20. The air path 16 also includes an input device 2, which is not related to the design of the gas turbine engine 1.

Behind the annular combustion chamber 20, a turbine 21 is installed and a gas path 22 is made, connecting the outlet from the annular combustion chamber 20 with the entrance to the free turbine 4.

Compressor 18 contains several stages, each of which contains a guide vane 23 and an impeller 24 (Fig. 1). The turbine 21 contains at least one stage. Each compressor stage 18 contains a nozzle apparatus 25 and an impeller 26.

The annular combustion chamber 20 contains a flame tube 27, a nozzle plate 28 with nozzles 29 and a fuel manifold 30 in front of the nozzle plate 28, designed to supply fuel gas to the nozzles 29 through special channels in the nozzle plate 28.

The structure of the annular combustion chamber 20 will be described in more detail below with reference to FIG. 2.

The drive shaft 31 connects the impellers 24 of the compressor 18 and the impeller 26 of the turbine 21 and is mounted on the first and second supports 32 and 33. There can be more than two supports for multi-shaft engines.

The fuel gas supply system includes a main fuel line 34, one end of which is connected to the outlet gas pipe 15, and the other end to the fuel manifold 30 of the combustion chamber 20. The main fuel line 34 contains a preheat exchanger 35 and a flow controller 36. Thus, the supply of the annular chamber combustion of 20 GPA fuel is carried out by gas pumped by the turbopump unit itself, i.e. from the outlet gas pipe 15.

The synthesis gas supply system comprises (FIGS. 3 and 4) a second gas line 37 connected to the main fuel line 34 after the preheating heat exchanger 35, a second valve 38 at the inlet to the second gas line 37.

The outlet from the second gas line 37 is connected to the second manifold 39, which is located in the engine path in front of the fuel manifold 30.

The same system includes an ejector fuel line 40 connected on one side to the outlet gas pipe 15, and on the other hand to an ejector-mixer 41. The ejector fuel line 40 has an ejection valve 42,

The final heat exchanger 43 is installed in the annular combustion chamber 20 for maximum efficiency. The inlet of the ejector fuel line 40 is connected to the outlet gas pipe 15, and the outlet is connected to one of the inlets to the ejector mixer 41 (FIGS. 1 and 2).

The fuel ejector line 40 is designed to supply relatively cold but highly pressurized fuel gas to the ejector-mixer 41 for its efficient operation as a mixer.

The final heating heat exchanger 43 (FIGS. 2 and 3) is located inside the annular combustion chamber 20, more precisely inside its flame tube 27 on its outer flame tube 44 and contains synthesis gas nozzles 45 and in the form of holes leading into the flame tube 27. Fuel channel The heat exchanger 46 is formed between the outer annular wall of which is part of the outer flame tube 46 and the inner flame tube and is connected at the inlet to the second manifold 39 and at the outlet with synthesis gas nozzles 45.

The final heating heat exchanger 43 (the first option) contains ribs 49 (Fig. 3 and Fig. 6) on the inner annular wall 48 from the side of the cavity of the flame tube 27.

To reduce aerodynamic losses, the final heating heat exchanger 43 may have lamellar longitudinal ribs (Fig. 6), but it is possible to use fins 49 in the form of cylinders 51 (Fig. 7) or in the form of cones 52 (Fig. 8). Catalyst 50 can be installed in the fuel channel of the heat exchanger 46.

In the final heating heat exchanger 43, the fuel gas is heated to 800°...900°C and turns into synthesis gas, which is more active in the oxidation process than fuel gas.

At the same time, it is important that excessively developed ribs do not introduce significant aerodynamic losses in terms of combustion products in the combustion chamber 20, which will worsen the overall efficiency of the gas-pumping unit. However, the use of fins will reduce the dimensions of the final heating heat exchanger 43 by another 2-3 times and increase the efficiency of this heat exchanger.

In FIG. 4 and 5 shows the gas-air nozzle 29.

It contains: shank 53, which is part of the body 54, outlet 55, guide vanes 56, inclined channels 57 for swirling air.

The fuel ejector line 40 can be equipped (FIGS. 1 and 2) with an ejector gearbox 58 and an ejector nozzle 59.

UNIT OPERATION

When starting the gas turbine engine 1 starter (not shown) untwist the drive shaft 31, which spins the impeller 7 of the compressor 18 (Fig. 1).

Fuel gas through the fuel line 34 through the flow regulator 35 and the valve 36 enters the cavity of the fuel manifold 30 and then enters the gas-air nozzle 29 (Fig. 1 and 2).

At the same time, part of the fuel gas in a volume of about 10% ... 30% of the total volume going into the annular combustion chamber 20 of the gas compressor unit, through the second gas line 37 through the ejector line of the fuel, enters the ejector-mixer 41 in which it is mixed with fuel with a relatively low temperature, but high pressure and is supplied to the preheating heat exchanger 35 (Fig. 1 and 2) then to the final heating heat exchanger 43, where the fuel gas is converted into synthesis gas and through the synthesis gas nozzles 45 enters the annular combustion chamber 20, more precisely directly into its fire tube 27.

In the preheating heat exchanger 35, the fuel gas is heated to 450°...500°C, and in the final heating heat exchanger 43 to 800...900°C and turns into synthesis gas, more active than the fuel gas. In catalyst 50 (FIG. 3), synthesis gas is further activated.

The location of the heat exchanger in the flame tube 27 of the annular combustion chamber 20 will make it possible to reduce its weight as much as possible and increase its efficiency by 2–3 times due to the very high temperature of the combustion products, which in modern gas turbine engines reaches 1500°C.

At the same time, the final heating heat exchanger 43 has a low aerodynamic resistance and does not impair the characteristics of the gas turbine engine 1 and the gas compressor unit as a whole.

As a result, despite the relatively small amount of synthesis gas, it evenly mixes with air and fuel gas in the combustion zone and activates the combustion process throughout the entire volume of the flame tube 27. The location of the synthesis gas nozzles 45 directly in the flame tube 27 prevents the recombination of ions and synthesis radicals. -gas and increases the completeness of combustion. This is also facilitated by the fact that a large number of small synthesis gas nozzles 45 are used, in the form of holes in the inner annular wall 48 in the final heating heat exchanger 43.

At the same time, when the gas turbine engine 1 is started, the shaft 9 and the free turbine 4 with the blower compressor 10 are spun, which increases the pressure of the pumped gas.

The application of the invention allowed:

- significantly increase the efficiency of the unit due to the greater activity of the synthesis gas, and the preservation of this activity after supply to the combustion zone due to the minimum proximity of the heat exchanger of the synthesis gas injectors to the internal cavity of the combustion chamber, namely the cavity of its flame tube, and the optimal location of the catalyst,

- increase the degree of heating of the fuel gas in the heat exchanger, which is easier to implement, since, firstly, the maximum value of the temperature of the combustion products in the engine takes place in the combustion zone of the flame tube, and secondly, the fuel gas is preheated in the preheating heat exchanger,

- reduce the dimensions of the final heating heat exchanger due to the large temperature difference on the walls of this heat exchanger, installed in the zone of the highest temperatures in the gas compressor unit,

- to prevent burnout of the final heating heat exchanger by using the fuel ejector line with relatively cold fuel.

Claims (5)

1. A gas compressor unit containing a gas turbine engine, an inlet device, a compressor, an annular combustion chamber with a flame tube having an external flame wall and fuel-air nozzles on the nozzle plate connected through a fuel manifold to the main fuel line, a turbine, a free turbine and an exhaust device, a synthesis gas system, which contains a gas extraction system and an ejector line with an ejector-mixer, to which the outlets of the gas extraction system and an ejector line are connected, a preheating heat exchanger installed in the exhaust device is connected to the inlet from the ejector-mixer, and to the outlet of the ejector - mixer, a final heating heat exchanger with a catalyst is connected through the second manifold, characterized in that the ejector line is made in the form of a fuel ejector line, the final heating heat exchanger is installed inside the flame tube on its outer flame wall and is equipped with synthesis gas injectors, and The lyzer is installed in the fuel channel of this heat exchanger. 2. The gas compressor unit according to claim 1, characterized in that the final heating heat exchanger has ribs on the inner wall. 3. Gas pumping unit according to claim 2, characterized in that the ribs are made in the form of longitudinal plates. 4. Gas pumping unit according to claim 2, characterized in that the ribs are made in the form of cylinders. 5. Gas pumping unit according to claim 2, characterized in that the ribs are made in the form of cones.

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