CN204388127U - Natural gas fuel gas turbine toroidal combustion chamber - Google Patents

Abstract

The utility model provides an annular combustion chamber of a natural gas fuel gas turbine. The combustion chamber shell is composed of four symmetrical parts, each part is respectively fixed on the high-pressure compressor load-bearing casing and the high-pressure turbine load-bearing casing by bolts, and there are thirty-six installation holes evenly distributed on the combustion chamber shell for connecting Thirty-six premixing sections, all of which are equipped with deflectors, each premixing section has a nozzle installation hole at the front end, and the nozzles are respectively installed in the nozzle installation holes at the front end of the premixing section; the diffuser and the premixing section The mixing section is connected by a transfer section, and each transfer section has a main air inlet, a cooling air inlet, a combustion air inlet, a cooling air outlet and a high-temperature gas channel; A cooling ring is formed between the casing, the high-pressure turbine load-bearing casing and the transition section. It ensures the stable working performance of the combustion chamber of the gas turbine, and is easy to disassemble and assemble, which is convenient for the maintenance and repair of the combustion chamber of the gas turbine after use.

Description

Natural gas fueled gas turbine annular combustor

Technical field:

The utility model relates to the field of heat energy and power engineering control, in particular to an annular combustion chamber of a natural gas fuel gas turbine.

Background technique:

Since the gas turbine came out in the early 1940s, because of its advantages such as high power, high efficiency, small size, quick start, smooth operation, simple operation, convenient maintenance, and reliable operation, it has been developed in just over half a century. China has achieved rapid development, and has been increasingly widely used in many fields such as electric power, petrochemical, transportation, metallurgy, and military affairs in various countries in the world. The level of gas turbine technology has become one of the important symbols of a country's technological level and military strength.

The annular combustion chamber has a series of advantages such as small size, light weight, small flow resistance loss, convenient cross-fire, less exhaust smoke, small heating area of the flame tube, and great development potential. It is a promising structural type . It is especially suitable for working with axial flow compressors. However, because the combustion space communicates with each other, the airflow and the combustion torch are not easy to organize, and the combustion performance is more difficult to control. The temperature field of the gas outlet is greatly affected by the airflow field and is not easy to maintain stability. At the same time, because the full-scale physical test requires a large power The air source, but the rigidity of the structure is poor, and it is not easy to disassemble and inspect the unit, so that this kind of combustion chamber has not been widely used for a long time, but it is currently developing rapidly.

According to a series of unfavorable factors of the above-mentioned annular combustion chamber, Guanghan Gas Turbine Co., Ltd. carried out a large number of theoretical and experimental researches in 2014, realizing low flow resistance loss, stable combustion and uniform outlet temperature when the annular combustion chamber communicates with each other in the combustion space At the same time, it also realizes the characteristics of easy disassembly and assembly of the annular combustion chamber.

Utility model content:

The utility model aims to solve the technical problems such as the difficulty in organizing the airflow and the combustion torch in the annular combustion chamber, the large influence of the gas outlet temperature field by the inlet airflow field, and the inconvenient decomposition inspection, etc., and provides a combustion stable, uniform outlet temperature, and easy to decompose. An annular combustion chamber structure that is assembled and convenient for local maintenance and repair after use.

The technical scheme of the utility model is: the annular combustion chamber of a natural gas fuel gas turbine includes a combustion chamber shell, and the entire combustion chamber shell is fixed on the load-bearing casing of the high-pressure compressor and the load-bearing casing of the high-pressure turbine with bolts, and the casing of the combustion chamber is composed of symmetrical four Each part is fixed on the load-bearing casing of the high-pressure compressor and the load-bearing casing of the high-pressure turbine by bolts. There are 36 installation holes evenly distributed on the combustion chamber shell, which are used to connect 36 pre-mixed There are deflectors in the thirty-six premixing sections, and each premixing section has a nozzle installation hole at the front end, and the thirty-six nozzles are respectively installed in the nozzle installation holes at the front end of the thirty-six premixing sections ; Thirty-six diffusers and thirty-six premixing sections are respectively connected through thirty-six transition sections, and each transition section has a main air inlet, cooling air inlet, combustion air inlet, and cooling air outlet and high-temperature gas channels; a cooling ring is formed between the combustion chamber casing, the combustion chamber casing, the high-pressure compressor load-bearing casing, the high-pressure turbine load-bearing casing and the transition section.

The casing of the combustion chamber is composed of four symmetrical parts, and each part is fixed and assembled into a ring by bolts. Each part has seven cooling ribs, and there are two mounting holes on the casing of the combustion chamber to install the igniter.

The inner surface of the combustion chamber casing has a thermal insulation coating.

The utility model has the following beneficial effects: 1. The casing of the combustion chamber adopts a split structure in which four symmetrical parts are assembled into a ring, and there are cooling ribs on it; the split structure realizes the disassembly and assembly of a single part of the combustion chamber without affecting The rest of the gas turbine; the heat dissipation ribs make the wall of the combustion chamber have better heat dissipation function and reduce the temperature of the wall of the combustion chamber; 2. The casing of the combustion chamber adopts a split structure with four symmetrical parts assembled into a ring, and the inner wall is equipped with a heat-insulating coating. The shell split structure is also to realize the disassembly and assembly of a single part of the combustion chamber. The heat insulation coating on the inner wall realizes the reduction of the temperature of the outer wall surface of the combustion chamber shell; A cooling ring is formed between the high-pressure turbine load-bearing casing and the transition section, and the combustion chamber casing, high-pressure compressor load-bearing casing, and high-pressure turbine load-bearing casing are isolated from the combustion chamber casing by cooling air, reducing the combustion chamber casing. 1. The surface temperature of the bearing casing of the high-pressure compressor and the bearing casing of the high-pressure turbine; 4. The nozzle is installed at the front end of the premixing section, and the internal deflector of the premixing section is used to fully mix the gas entering from the nozzle and the compressed air to ensure The outlet temperature distribution of the combustion chamber is uniform.

Description of drawings:

Fig. 1 is a structural representation of the utility model;

Accompanying drawing 2 is A-A sectional view of accompanying drawing 1;

Accompanying drawing 3 is the structural front view of the premix section in the utility model;

Accompanying drawing 4 is the main cross-sectional view of the structure of the transition section in the utility model.

In the figure, 1-combustion chamber casing, 2-combustion chamber casing, 3-high-pressure compressor casing, 4-premixing section, 5-nozzle, 6-high-pressure turbine casing, 7-transition section, 8 -diffuser, 9-insulation coating, 10-cooling air outlet, 11-cooling ring, 12-cooling air inlet, 13-radiating fins, 14-igniter, 15-nozzle mounting hole, 16-guide Flow plate, 17-main air inlet, 18-combustion air inlet, 19-cooling channel, 20-high temperature gas channel.

Detailed ways:

Below in conjunction with accompanying drawing, the utility model is further described:

As shown in Fig. 1 combined with Fig. 2 to Fig. 4, the annular combustor of a natural gas fueled gas turbine includes a combustor shell 1, and the entire combustor shell 1 is fixed to the high-pressure compressor load-bearing casing 3 and the high-pressure turbine load-bearing casing 6 with bolts. Above, the combustor casing 2 is composed of four symmetrical parts, and each part is respectively fixed on the high-pressure compressor load-bearing casing 3 and the high-pressure turbine load-bearing casing 6 by bolts. Mounting holes for connecting thirty-six premixing sections 4, thirty-six premixing sections 4 are equipped with deflectors 16, each premixing section 4 front end has a nozzle installation hole 15, thirty-six The nozzles 5 are respectively installed in the nozzle mounting holes 15 at the front ends of the thirty-six premixing sections 4; the thirty-six diffusers 8 and the thirty-six premixing sections 4 are respectively connected through thirty-six transition sections 7, Each transition section 7 has main air inlet 17, cooling air inlet 12, combustion air inlet 18, cooling air outlet 10 and high-temperature gas channel 20; combustion chamber shell 2, combustion chamber shell 1, high-pressure compressor bearing machine A cooling ring 11 is formed between the casing 3 , the high-pressure turbine load-bearing casing 6 and the transition section 7 .

Combustion chamber casing 1 is made up of four symmetrical parts, and each part is assembled into a ring by bolts, and each part has seven cooling ribs 13, and two installation holes are arranged on combustion chamber casing 1, are used for installing igniter 14.

The inner surface of the combustion chamber casing 2 is provided with a thermal insulation coating 9 .

The cooling air enters from the cooling air inlet 12 of the transition section 7, and flows through the cavity formed by the combustion chamber casing 2 and the high-pressure turbine load-bearing casing 6, the cavity formed by the combustion chamber casing 2 and the combustion chamber casing 1, and the combustion chamber respectively. The cavity formed by the inner shell 2 and the high-pressure compressor load-bearing casing 3 finally flows into the cooling channel 19 of the transition section 7 and flows out from the cooling air outlet 10 .

Claims (3)

1. A natural gas fuel gas turbine annular combustor, comprising a combustor shell (1), is characterized in that: the whole combustor shell (1) is bolted to a high-pressure compressor load-bearing casing (3) and a high-pressure turbine load-bearing On the casing (6), the combustion chamber casing (2) is composed of four symmetrical parts, and each part is fixed on the high-pressure compressor load-bearing casing (3) and the high-pressure turbine load-bearing casing (6) respectively by bolts. There are thirty-six installation holes evenly distributed on the shell (2), which are used to connect thirty-six premixing sections (4), and there are deflectors (16) in the thirty-six premixing sections (4) , each premixing section (4) has a nozzle mounting hole (15) at the front end, and thirty-six nozzles (5) are respectively installed in the nozzle mounting holes (15) at the front end of the thirty-six premixing section (4); Thirty-six diffusers (8) and thirty-six premixing sections (4) are respectively connected through thirty-six transition sections (7), and each transition section (7) has a main air inlet ( 17), cooling air inlet (12), combustion air inlet (18), cooling air outlet (10) and high temperature gas channel (20); combustion chamber shell (2), combustion chamber shell (1), high pressure compressor bearing A cooling ring (11) is formed between the casing (3), the high-pressure turbine load-bearing casing (6) and the transition section (7). 2. The annular combustor of natural gas fuel gas turbine according to claim 1, characterized in that: the combustor shell (1) is composed of four symmetrical parts, each part is fixed and assembled into a ring by bolts, and each part has seven cooling ribs Sheet (13), there are two mounting holes on the combustion chamber housing (1) to install the igniter (14). 3. The annular combustor of natural gas fuel gas turbine according to claim 1, characterized in that: the inner surface of the combustor inner casing (2) is provided with a thermal insulation coating (9).