CN220205812U - 18MW grade gas turbine combustion chamber structure suitable for liquid fuel - Google Patents

Abstract

The utility model discloses an 18 MW-level gas turbine combustion chamber structure suitable for liquid fuel, belongs to the technical field of combustion chambers, and aims to solve the problem of high air flow velocity in front of a flame tube. The high-pressure gas turbine comprises a front conical barrel and a rear conical barrel which are integrally connected, wherein an outer cover shell is sleeved on the periphery of the inner cover shell, the inner cover shell and the outer cover shell are respectively connected with the front conical barrel, the rear end of a high-pressure gas turbine is connected with a two-stage annular diffuser, a plurality of flame barrels and a plurality of mixers are circumferentially arranged in a combustion chamber and are connected in a one-to-one correspondence manner, the flame barrels are fixed on the front conical barrel, a plurality of ejectors are circumferentially arranged on the front conical barrel and are connected with the flame barrels in a one-to-one correspondence manner, a first-stage oil pipe is connected with the ejectors through a first supply pipe, the flame barrels are sequentially connected in series end-to-end manner through flame connecting pipes, and two flame connecting pipes are correspondingly connected with two igniters. The two-stage annular diffuser is arranged, so that the front air flow velocity of the flame tube can be effectively reduced.

Description

18MW grade gas turbine combustion chamber structure suitable for liquid fuel

Technical Field

The utility model belongs to the technical field of combustion chambers, and particularly relates to an 18 MW-grade gas turbine combustion chamber structure suitable for liquid fuel.

Background

The combustor is a device in which fuel or propellant is combusted to produce high temperature gas, and is an important component of a gas turbine. The combustion chamber is composed of a diffuser, a combustion chamber shell, a flame tube, a fuel nozzle and an ignition device.

The 18MW grade gas turbine combustor of the existing liquid fuel has the following problems:

1. the air flow speed in front of the flame tube is high;

2. the flame tube in the combustion chamber is unevenly ignited.

Disclosure of Invention

The utility model aims to provide an 18 MW-grade gas turbine combustion chamber structure suitable for liquid fuel, so as to solve the problems of high air flow speed in front of a flame tube of the existing liquid fuel combustion chamber and uneven ignition of the flame tube in the combustion chamber. The technical scheme adopted by the utility model is as follows:

an 18MW grade gas turbine combustion chamber structure suitable for liquid fuel comprises a two-stage annular diffuser, a power shell, a front cone-shaped bobbin, a plurality of flame tubes, an outer housing and an inner housing; the front end of the front cone-shaped bobbin is integrally connected with the rear end of the power shell, the power shell is connected with the inner cover shell in a front-rear mode and sleeved on the periphery of the high-pressure compressor, the rear end of the high-pressure compressor is connected with the two-stage annular diffuser, the outlet outer ring of the two-stage annular diffuser is connected with the rear end of the inner cover shell, the outer cover shell is sleeved on the periphery of the inner cover shell, the front end of the outer cover shell is connected with the rear end of the front cone-shaped bobbin, an annular combustion chamber is formed between the inner cover shell and the outer cover shell, a plurality of flame tubes and a plurality of mixers are circumferentially arranged in the combustion chamber, the flame tubes correspond to the mixers one by one, the rear end of each flame tube is provided with a telescopic ring, the front end of each mixer is provided with a front ring, the inner periphery of each telescopic ring is in sliding fit with the outer Zhou Chajie of the front ring, the flame tube is fixed at the rear end of the front cone-shaped tube through a positioner inserted into the flame tube, the rear end of the mixer is connected with a high-pressure turbine spray tube device, a suspension bracket is arranged on a power shell, a first-stage oil tube and a second-stage oil tube are respectively fixed on the suspension bracket, a plurality of ejectors are circumferentially arranged on the front cone-shaped tube, the front end of the flame tube is provided with a cyclone, the ejectors are connected with the cyclones of the flame tube in a one-to-one correspondence manner, the first-stage oil tube is connected with the ejectors through a first supply tube, the second-stage oil tube is connected with the rest needed oil device through a second supply tube, the flame tubes are sequentially connected in series end to end through flame tubes, and two flame tubes are correspondingly connected with two igniters.

Further, sixteen flame tubes are provided.

Further, a plurality of flame tubes are uniformly arranged.

Further, the outer housing is detachably connected with the front cone-shaped bobbin.

Further, a valve is arranged on the outer housing.

Compared with the prior art, the utility model has the beneficial effects that:

1. the two-stage annular diffuser is arranged, so that the front air flow velocity of the flame tube can be effectively reduced.

2. The first-stage oil pipe and the second-stage oil pipe ensure the safety function in the starting state and the running state.

3. The number of mixers and ejectors is determined by the power of the complete machine and the compressor flow.

4. The two igniters are arranged to ensure stable ignition, and the circumferential flame connecting pipes are arranged to ensure that each flame tube can be ignited rapidly.

Drawings

FIG. 1 is a schematic diagram of the structure of the present utility model;

FIG. 2 is a cross-sectional view of a combustion chamber.

In the figure: 1-two-stage annular diffuser, 2-power shell, 3-outer housing, 4-inner housing, 5-flame tube, 6-mixer, 7-injector, 8-valve, 9-suspension bracket, 10-first stage oil pipe, 11-second stage oil pipe, 12-igniter, 13-first supply pipe, 14-second supply pipe, 15-continuous flame pipe, 16-front cone tube and 17-high pressure compressor.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, the present utility model is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the utility model. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present utility model.

The connection mentioned in the utility model is divided into fixed connection and detachable connection, wherein the fixed connection is a conventional fixed connection mode such as folding connection, rivet connection, bonding connection, welding connection and the like, the detachable connection comprises a conventional detachable mode such as bolt connection, buckle connection, pin connection, hinge connection and the like, and when a specific connection mode is not limited, at least one connection mode can be found in the conventional connection mode by default to realize the function, and the person skilled in the art can select the function according to the needs. For example: the fixed connection is welded connection, and the detachable connection is bolted connection.

The present utility model will be described in further detail below with reference to the accompanying drawings, the following examples being illustrative of the present utility model and the present utility model is not limited to the following examples.

Examples: as shown in fig. 1 and 2, an 18MW grade gas turbine combustor structure suitable for liquid fuel comprises a two-stage annular diffuser 1, a power housing 2, a front cone 16, a plurality of flame tubes 5, an outer casing 3 and an inner casing 4; the front end of the front cone-shaped bobbin 16 is integrally connected with the rear end of the power shell 2, the power shell 2 and the inner cover shell 4 are connected in a front-back mode and sleeved on the periphery of the high-pressure air compressor 17, the rear end of the high-pressure air compressor 17 is connected with the two-stage annular diffuser 1, the outlet outer ring of the two-stage annular diffuser 1 is connected with the rear end of the inner cover shell 4, the outer cover shell 3 is sleeved on the periphery of the inner cover shell 4, the front end of the outer cover shell 3 is connected with the rear end of the front cone-shaped bobbin 16, an annular combustion chamber is formed between the inner cover shell 4 and the outer cover shell 3, a plurality of flame tubes 5 and a plurality of mixers 6 are circumferentially arranged in the combustion chamber, the flame tubes 5 and the mixers 6 are in one-to-one correspondence, the rear end of the flame tubes 5 is provided with a telescopic ring, the front end of the mixers 6 is provided with a front ring, the inner periphery of the telescopic ring is in sliding fit with the outer Zhou Chajie of the front ring, the flame tube 5 is fixed at the rear end of a front cone-shaped tube 16 through a positioner inserted into the flame tube, the rear end of the mixer 6 is connected with a high-pressure turbine spray pipe device, a suspension bracket 9 is arranged on the power shell 2, a first-stage oil pipe 10 and a second-stage oil pipe 11 are respectively fixed on the suspension bracket 9, a plurality of ejectors 7 are circumferentially arranged on the front cone-shaped tube 16, the front end of the flame tube 5 is provided with a swirler, the ejectors 7 are connected with the swirlers of the flame tube in a one-to-one correspondence manner, the first-stage oil pipe 10 is connected with the ejectors 7 through a first supply pipe 13, the second-stage oil pipe 11 is connected with the rest needed oil device through a second supply pipe 14, the flame tubes 5 are sequentially connected in series end to end through flame tubes 15, and two flame tubes 15 are correspondingly connected with two igniters 12.

Sixteen cartridges 5 are provided.

The flame tubes 5 are uniformly arranged.

The outer housing 3 is detachably connected to the front cone bobbin 16.

The outer housing 3 is provided with a valve 8.

When the gas generator is started, the fuel in the flame tube 5 is ignited by the two igniters 12. Each igniter 12 ignites the mixture of fuel and air in both cartridges 5. The flames between the several cartridges 5 are conveyed through a crossfire tube 15. Fuel is fed and injected in the liner 5 by sixteen centrifugal two-channel injectors 7. When the whole machine is started, liquid fuel is discharged from the first-stage oil pipe 10 and is fed to the first channel of the injector 7 along the first supply pipe 13. The rest of the whole machine operation modes are ensured by the fuel fed from the first stage oil pipe 10 and the second stage oil pipe 11 through the first supply pipe 13 and the second supply pipe 14. In order to improve the injection of fuel, high-pressure air is fed into the second passage of the injector 7 at start-up. After the complete machine runs in no-load, the air supply to the ejector 7 is stopped. The outer casing 3 of the combustion chamber is made in the form of a cylinder, provided with a flange at the end.

The utility model relates to a combustion chamber structure of a gas turbine, wherein a high-pressure compressor is utilized to continuously supply high-pressure air flow to the combustion chamber, the combustion chamber is combusted with fuel injected by the combustion chamber to form a high-temperature high-pressure heat source, turbine blades are pushed to rotate to do work, the combustion chamber structure is suitable for liquid fuel, a liquid fuel supply system can be efficiently and stably started and effectively organized, and an annular space is provided for combustion.

The utility model has the advantages that:

1. the two-stage annular diffuser 1 is arranged, so that the front air flow speed of the flame tube 5 can be effectively reduced.

2. The first-stage oil pipe 10 and the second-stage oil pipe 11 ensure safety functions in the start-up state and the running state.

3. The number of mixers 6 and ejectors 7 is determined by the power of the whole machine and the compressor flow.

4. The two igniters 12 are arranged to ensure stable ignition, and the Zhou Xianglian flame tubes 15 are arranged to ensure that each flame tube 5 can be ignited quickly.

The above embodiments are only illustrative of the present utility model and do not limit the scope thereof, and those skilled in the art may also make modifications to parts thereof without departing from the spirit of the utility model.

Claims (5)

1. An 18MW grade gas turbine combustor structure adapted for liquid fuel, characterized by: comprises a two-stage annular diffuser (1), a power shell (2), a front conical tube (16), a plurality of flame tubes (5), an outer cover shell (3) and an inner cover shell (4); the front end of the front cone-shaped bobbin (16) is integrally connected with the rear end of the power shell (2), the power shell (2) is connected with the front and rear ends of the inner cover shell (4) and sleeved on the periphery of the high-pressure air compressor (17), the rear end of the high-pressure air compressor (17) is connected with the two-stage annular diffuser (1), the outlet outer ring of the two-stage annular diffuser (1) is connected with the rear end of the inner cover shell (4), the outer cover shell (3) is sleeved on the periphery of the inner cover shell (4), the front end of the outer cover shell (3) is connected with the rear end of the front cone-shaped bobbin (16), an annular combustion chamber is formed between the inner cover shell (4) and the outer cover shell (3), a plurality of flame tubes (5) and a plurality of mixers (6) are circumferentially arranged in the combustion chamber, the flame tubes (5) and the mixers (6) are in one-to-one correspondence, the rear end of the flame tube (5) is provided with a telescopic ring, the front end of the mixer (6) is provided with a front ring, the inner periphery of the telescopic ring is in sliding fit with the outer Zhou Chajie of the front ring, the flame tube (5) is fixed at the rear end of a front conical tube (16) through a positioner inserted into the telescopic ring, the rear end of the mixer (6) is connected with a high-pressure turbine spray pipe device, a hanging frame (9) is arranged on a power shell (2), a first-stage oil pipe (10) and a second-stage oil pipe (11) are respectively fixed on the hanging frame (9), the circumference is provided with a plurality of ejectors (7) on preceding toper bobbin (16), and the front end of flame tube (5) is equipped with the swirler, and a plurality of ejectors (7) link to each other with the swirler one-to-one of a plurality of flame tubes, and first level oil pipe (10) link to each other with a plurality of ejectors (7) through first supply pipe (13), and second level oil pipe (11) link to each other with the device of the rest needs oil through second supply pipe (14), concatenate in proper order end to end through linking flame pipe (15) between a plurality of flame tube (5), and two of them each link flame pipe (15) and two igniters (12) and link to each other.

2. An 18MW grade gas turbine combustor structure for liquid fuels as set forth in claim 1, wherein: sixteen flame tubes (5) are arranged.

3. An 18MW grade gas turbine combustor structure for liquid fuels as set forth in claim 2, wherein: the flame tubes (5) are uniformly arranged.

4. An 18MW grade gas turbine combustor structure for liquid fuels according to claim 3, wherein: the outer housing (3) is detachably connected with the front conical bobbin (16).

5. An 18MW grade gas turbine combustor structure for liquid fuels according to any of claims 1-4, wherein: the outer housing (3) is provided with a valve (8).