Gas entraining anti-icing structure of gas turbine

Abstract

The utility model relates to an air-entraining anti-icing structure of a gas turbine, which relates to the field of marine gas turbines and adopts a pipeline type structure, a starting point of a pipeline is connected with an intermediate stage of a gas compressor of the gas turbine, and an end point of the pipeline is led to an air inlet of the gas compressor; the pipeline comprises an electrically operated valve air-entraining flow measuring section, an air-entraining pipe, an air-entraining injection branch pipe and a plurality of spiral nozzles which are arranged in sequence, and airflow with heat energy is dispersed and input into the air inlet pipeline of the air compressor. When the humidity of an inlet of a gas compressor reaches 100%, the temperature of the inlet of the gas compressor is lower than 0 DEG C and the condition of icing is met, an air entraining anti-icing structure needs to be put into the air entraining anti-icing structure, the opening degree of an electric valve is adjusted by adjusting an anti-icing system, and the amount of hot air needed by putting is adjusted, so that the situation that unnecessary efficiency reduction is caused by too early putting into the gas turbine is avoided.

Description

Technical Field

[0001] This utility model relates to the field of marine gas turbine technology, and in particular to a gas turbine bleed air anti-icing structure. Background Technology

[0002] Gas turbines, as a power source, are widely used in marine propulsion and offshore platforms. During operation, the drastic changes in intake air velocity at the gas turbine inlet lead to significant variations in intake air temperature, converting the internal energy of the air into its kinetic energy. Due to the reduced cross-section and increased air velocity at the compressor inlet, the intake air temperature decreases; some water vapor in the air condenses into water. This condensate freezes below its freezing point. Because of the high velocity at the compressor inlet, and for safety reasons, it is not advisable to measure the local relative humidity during prolonged operation.

[0003] Gas turbines typically use bleed air from the intermediate stage of the compressor to introduce high-temperature, high-pressure air into the intake duct to heat the air and prevent icing. However, bleed air reduces the efficiency of the gas turbine, requiring precise early warning: whether the bleed air anti-icing system needs to be activated under real-time operating conditions to prevent premature activation and unnecessary efficiency reduction of the gas turbine. Utility Model Content

[0004] In response to the shortcomings of the existing production technology, the applicant provides a gas turbine bleed air anti-icing structure, which is used to guide the high-temperature and high-pressure gas from the intermediate stage of the compressor to the compressor inlet, mix it with filtered high-humidity and cold air, and then re-enter the gas turbine to prevent the gas turbine from malfunctioning.

[0005] The technical solution adopted in this utility model is as follows:

[0006] A gas turbine bleed air anti-icing structure is provided, which adopts a pipeline structure. The starting point of the pipeline is connected to the intermediate stage of the gas turbine compressor, and the ending point of the pipeline is led to the air inlet of the compressor. The pipeline includes an electric valve bleed air flow measurement section, a bleed air pipe, a bleed air injection branch pipe, and a spiral nozzle arranged in sequence. Multiple spiral nozzles are provided to disperse the airflow with heat energy into the compressor air inlet pipeline.

[0007] As a further improvement to the above technical solution:

[0008] A support is installed on the inner wall of the compressor's intake pipe, and the bleed air injection branch pipe and spiral nozzle are mounted on the support.

[0009] The spiral nozzles on the support are arranged in an array in the vertical plane, and the vertical height of the hot gas output surface where the spiral nozzles are located is approximately the height of the compressor inlet.

[0010] The air duct is provided in multiple sections, arranged in a vertical array, and all of them are connected to the horizontally arranged air duct.

[0011] The spiral nozzles are arranged in an array at equal intervals on each induced draft jet branch pipe, or staggered on two adjacent induced draft jet branch pipes.

[0012] Total temperature and total pressure probes and pipeline static pressure measuring points are set on the bleed air flow measurement section.

[0013] The static pressure measuring points for the pipeline are symmetrically set on both sides of the pipeline.

[0014] The total temperature and total pressure probe is located at a point 10 times the diameter along the length of the bleed air flow measurement section in the air intake direction.

[0015] The total temperature and total pressure probe has a length of 5 times its diameter reserved on the side facing the airflow outflow direction.

[0016] The electric valve is connected to the outlet of the intermediate stage of the compressor to control the on / off flow of the hot air.

[0017] The beneficial effects of this utility model are as follows:

[0018] This utility model discloses a gas turbine bleed air anti-icing structure. When the compressor inlet temperature is below 0°C and the conditions for icing are met, the bleed air anti-icing system of this utility model is activated. The anti-icing system adjusts the opening of the electric valve to introduce the required amount of hot air, which can avoid premature activation and unnecessary efficiency reduction of the gas turbine. This is of great significance for the stable and efficient operation of the gas turbine. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the air intake anti-icing system of the present invention.

[0020] Figure 2 for Figure 1 The enlarged view of part A is used to illustrate the structure of the bleed air nozzle.

[0021] Figure 3 for Figure 2 A schematic diagram of the distribution of the central airway.

[0022] Figure 4 This is a schematic diagram of the air jet branch pipe arrangement of the present invention.

[0023] Figure 5 This is a schematic diagram of the air tube on which the probe is installed in this invention.

[0024] Figure 6 for Figure 5 The figure shows the BB cross-sectional view, which includes the total temperature and total pressure probes and the pipeline static pressure measuring points.

[0025] The components include: 1. Electric valve; 2. Air flow measurement section; 3. Air duct; 4. Air jet branch pipe; 5. Spiral nozzle; 6. Support; 7. Total temperature and total pressure probe; 8. Pipeline static pressure measuring point. Detailed Implementation

[0026] The specific embodiments of this utility model are described below with reference to the accompanying drawings.

[0027] like Figures 1-6 As shown, the gas turbine bleed air anti-icing structure of this embodiment adopts a pipeline structure. The starting point of the pipeline is connected to the intermediate stage of the gas turbine compressor, and the ending point of the pipeline is led to the air inlet of the compressor. The pipeline includes an electric valve 1, a bleed air flow measurement section 2, a bleed air pipe 3, a bleed air injection branch pipe 4, and a spiral nozzle 5 arranged in sequence. Multiple spiral nozzles 5 are provided to disperse the airflow with heat energy into the compressor air inlet pipeline.

[0028] A bracket 6 is installed on the inner wall of the compressor's intake pipe, and the induced draft branch pipe 4 and the spiral nozzle 5 are installed on the bracket 6.

[0029] The spiral nozzles 5 on the bracket 6 are arranged in an array in the vertical plane, and the vertical height of the hot gas output surface where the spiral nozzles 5 are located is close to the height of the compressor inlet.

[0030] There are multiple expiratory air jet branch pipes 4, which are arranged in a vertical array and are all connected to the horizontally arranged expiratory air pipes 3.

[0031] The spiral nozzles 5 are arranged in an array at equal intervals on each air injection branch pipe 4, or staggered on two adjacent air injection branch pipes 4.

[0032] Set up a total temperature and total pressure probe 7 and a pipeline static pressure measuring point 8 on the expiratory air flow measurement section 2.

[0033] The pipeline static pressure measuring points 8 are symmetrically set on both sides of the pipeline.

[0034] The total temperature and total pressure probe 7 is located at a point 10 times the diameter along the length of the intake direction of the bleed air flow measurement section 2.

[0035] The total temperature and total pressure probe 7 has a length of 5 times its diameter reserved on the side facing the airflow outflow direction.

[0036] Electric valve 1 is connected to the outlet of the intermediate stage of the compressor to control the on / off of the airflow carrying thermal energy.

[0037] This invention provides a gas turbine bleed air anti-icing system, which draws high-temperature and high-pressure gas from the intermediate stage of the compressor to the compressor inlet, mixes it with filtered high-humidity and cold air, and then re-enters the gas turbine for operation.

[0038] The induced draft anti-icing system is installed sequentially along the flow path of the high-temperature, high-pressure gas: such as... Figures 1-3As shown, the system includes an electric valve 1 connected to the outlet of the intermediate stage of the compressor, a bleed air flow measurement section 2, a bleed air pipe 3, a bleed air injection branch pipe 4, and a spiral nozzle 5. A bracket 6 is installed on the rigid wall between the compressor inlet and the filter on the inlet pipe. The bleed air injection branch pipe 4 and the spiral nozzle 5 are mounted on the bracket 6, and the outlet direction of the spiral nozzle 5 is towards the compressor inlet.

[0039] like Figure 4 As shown, multiple air jet branch pipes 4 are installed.

[0040] like Figure 5 and Figure 6 As shown, in the bleed air flow measurement section 2, a total temperature and total pressure probe 7 and a static pressure measuring point 8 of the measuring pipe are installed at a position 10 times the diameter along the length of the air intake direction; on the output side of the total temperature and total pressure probe 7 along the airflow direction, the bleed air measurement section has a length of 5 times the diameter.

[0041] The above description is an explanation of the present utility model and not a limitation thereof. The scope of the present utility model is defined by the claims. Within the protection scope of the present utility model, any form of modification may be made.

Claims

1. A gas turbine bleed air anti-icing structure, characterized in that: The pipeline adopts a pipeline structure. The starting point of the pipeline is connected to the intermediate stage of the gas turbine compressor, and the ending point of the pipeline is led to the air inlet of the compressor. The pipeline includes an electric valve (1), an air flow measurement section (2), an air bleed pipe (3), an air bleed injection branch pipe (4), and a spiral nozzle (5) arranged in sequence. Multiple spiral nozzles (5) are provided to disperse the airflow with heat energy into the air inlet pipeline of the compressor.

2. The gas turbine bleed air anti-icing structure as described in claim 1, characterized in that: A bracket (6) is installed on the inner wall of the compressor's intake pipe, and the induced draft branch pipe (4) and the spiral nozzle (5) are installed on the bracket (6).

3. The gas turbine bleed air anti-icing structure as described in claim 1, characterized in that: The spiral nozzles (5) on the bracket (6) are arranged in an array in the vertical plane, and the vertical height of the hot gas output surface where the spiral nozzles (5) are located is close to the height of the compressor inlet.

4. The gas turbine bleed air anti-icing structure as described in claim 3, characterized in that: The air jet branch pipe (4) is provided in multiple ways. The air jet branch pipe (4) is arranged in a vertical array and is connected to the horizontally arranged air jet pipe (3).

5. The gas turbine bleed air anti-icing structure as described in claim 4, characterized in that: The spiral nozzles (5) are arranged at equal intervals on each air injection branch pipe (4), or staggered on two adjacent air injection branch pipes (4).

6. The gas turbine bleed air anti-icing structure as described in claim 1, characterized in that: A total temperature and total pressure probe (7) and a pipeline static pressure measuring point (8) are set on the induced air flow measurement section (2).

7. The gas turbine bleed air anti-icing structure as described in claim 6, characterized in that: The static pressure measuring points (8) are symmetrically set on both sides of the pipeline.

8. The gas turbine bleed air anti-icing structure as described in claim 6, characterized in that: The total temperature and total pressure probe (7) is located at a point 10 times the diameter along the length of the intake direction of the bleed air flow measurement section (2).

9. The gas turbine bleed air anti-icing structure as described in claim 6, characterized in that: The total temperature and pressure probe (7) has a length of 5 times its diameter reserved on the side facing the airflow outflow direction.

10. The gas turbine bleed air anti-icing structure as described in claim 6, characterized in that: The electric valve (1) is connected to the outlet of the intermediate stage of the compressor to control the on / off of the airflow with heat energy.

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