Rotary turbine flow and cooling test device and method

Rotary turbine flow and cooling test device and method

  • CN 106,017,908 B
  • Filed: 07/28/2016
  • Issued: 01/19/2021
  • Est. Priority Date: 07/28/2016
  • Status: Active Grant
First Claim
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1. A rotary turbine flow and cooling test apparatus, comprising:

  • a turbine test main flow system (5) for extracting the exhaust gas of the compressor (2) of the power station gas turbine (1) as main flow air, burning the main flow air to form gas, and inputting the gas into the test turbine (12), a cooling air system (6) for extracting the exhaust gas of the compressor (2) of the power station gas turbine (1) as cooling air and cooling the test turbine (12), and a cooling water system (7) for cooling an intake pipe and an exhaust pipe of the test turbine (12);

    the turbine test main flow system (5) comprises a main flow air inlet valve (8), an air inlet regulating valve (9), an annular combustor (11), a test turbine (12), a hydraulic dynamometer (13), an exhaust desuperheater (14), an exhaust butterfly valve (15) and a silencing tower (16), wherein the main flow air inlet valve (8) is connected with a compressor (2) of a power station gas turbine (1), the main flow air inlet valve (8), the air inlet regulating valve (9), the annular combustor (11) and an air inlet pipeline of the test turbine (12) are sequentially connected, an exhaust pipeline of the test turbine (12) is connected with the exhaust desuperheater (14), the exhaust butterfly valve (15) and the silencing tower (16) are sequentially connected, and an output shaft of the turbine test (12) is connected with the hydraulic dynamometer (13);

    the cooling air system is connected with the test turbine (12), and the cooling water system is connected with the test turbine (12), the hydraulic dynamometer (13) and the exhaust desuperheater (14);

    the test turbine (12) comprises a double-layer cylinder consisting of an outer cylinder and an inner cylinder arranged in the outer cylinder, a water-cooling transition section (37) arranged at the front end of the double-layer cylinder and connected with the double-layer cylinder, and an exhaust volute (35) arranged at the rear end of the double-layer cylinder and connected with the double-layer cylinder, wherein the water-cooling transition section (37) and the exhaust volute (35) are respectively connected with an air inlet pipeline and an exhaust pipeline of the test turbine (12), a cooling water system is connected with the water-cooling transition section (37) and the exhaust volute (35) of the test turbine (12), the water-cooling transition section (37) is a double-layer pipeline, cooling water from the cooling water system is adopted between the double-layer pipelines, the exhaust volute is a double-layer shell, and cooling water from the cooling water system is;

    the outer cylinder is provided with a cooling air inlet communicated with the space between the outer cylinder and the inner cylinder, the water-cooling transition section (37) is provided with a cooling hole, and the cooling air system is communicated with the cooling air inlet on the outer cylinder and the cooling hole on the water-cooling transition section (37);

    the inner cylinder is internally provided with 1-4 stages of static blades and 1-4 stages of moving blades, each stage of static blade is provided with an internal cooling channel, the first stage of static blade is fixed on a static blade inner ring in the inner cylinder, the static blade inner ring is provided with an air inlet, the air inlet of the static blade inner ring is communicated with a cooling hole on a water-cooling transition section (37) and the internal cooling channel of the first stage of static blade, cooling air from a cooling air system can enter the internal cooling channel of the first stage of static blade through the cooling hole on the water-cooling transition section (37) and the air inlet of the static blade inner ring, the root of each stage of static blade is provided with an air inlet communicated with the space between the outer gas cylinder and the inner cylinder, and the cooling air from the cooling air system can enter the internal cooling channel of each stage of static blade from the air inlet at the root of each stage of static;

    the rotary turbine flow and cooling test apparatus further comprises;

    the device comprises a flow meter, a pressure measuring point and a temperature measuring point which are arranged on a pipeline between an annular combustor (11) and a metal expansion joint and are respectively used for measuring the flow, pressure and temperature of air in front of the annular combustor (11), a pressure measuring point and a temperature measuring point which are arranged on the pipeline between the annular combustor (11) and a test turbine (12) and are respectively used for measuring the pressure and temperature of gas behind the annular combustor (11), a temperature measuring point which is arranged on a turbine blade of the test turbine (12) and is used for measuring the metal temperature of the turbine blade of the test turbine (12), an air flow meter, a pressure measuring point and a temperature measuring point which are arranged on the pipeline between a cooling air regulating valve (18) and the test turbine (12) and are respectively used for measuring the flow, pressure and temperature of cooling air of a cooling air system (6);

    the moving blades are correspondingly arranged on the moving blades at each stage in the inner cylinder, the two sides of each moving blade are provided with static parts, a disc cavity is formed between each moving blade and the static parts at the two sides of each moving blade, each moving blade is provided with a cooling hole, the cooling hole of the water-cooling transition section is communicated with the disc cavity formed between each moving blade and the static parts at the two sides of each moving blade and the cooling hole on each moving blade, each moving blade is provided with an internal cooling channel, the root part of each moving blade is provided with an air inlet communicated with the internal cooling channel of the moving blade, the air inlet of the first moving blade is communicated with the disc cavity between the first moving blade and the static parts at the two sides of the first moving blade, cooling air from a cooling air system can sequentially pass through the cooling hole of the water-cooling transition section and the disc cavity between the first moving blade, the air inlet holes of other moving blades at each stage are communicated with the disc cavities between the corresponding impellers at each stage and the static parts at two sides of the impellers at each stage, and cooling air from a cooling air system can enter the internal cooling channel through the cooling holes on the impellers and the disc cavities between the impellers at each stage and the static parts at two sides of the impellers at each stage through the air inlet holes at the roots of the moving blades at other stages.

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