Gap measurement device for combustor, and gap measurement method

Abstract

The purpose of the present invention is to provide a gap measurement device (20) for a combustor (1) and a gap measurement method, with which the size of a gap between a first cylindrical body (2a) surrounding the periphery of a combustion nozzle, and a second cylindrical body (2b) which is connected to the first cylindrical body (2a) and which guides combustion gas to a down-stream side, can be measured when the combustor (1) is in an assembled state. This gap measurement device (20) for the combustor (1) is provided with: a rod member (30) which, in a state of being inserted inside the combustor (1), is attached to a first flange (1a) of the combustor (1), at least a base-end side of said rod member (30) being hollow; a support member (50) attached to a tip of the rod member (30) so as to be capable of rotating about a shaft core (55) orthogonal to the axial direction of the rod member (30); an imaging element (60) which is supported on the support member (50), and which images an annular gap (19); an operation lever (70) which passes through the inside of the rod member (30), and which extends towards the support member (50); and a link mechanism (80) which is provided between the operation lever (70) and the support member (50), and which converts back-and-forth movement of the operation lever (70) into rotational movement of the support member about the shaft core (55).

Description

technical field [0001] The invention relates to a gap measuring device and a gap measuring method for a burner. Background technique [0002] Conventionally, gas turbine combustors having various structures are known. [0003] A typical structure of a gas turbine combustor includes: a pilot nozzle, a plurality of main nozzles arranged at equal intervals around the outer periphery of the pilot nozzle, and a nozzle provided so as to cover the downstream front end portion of the main nozzle. main burner. Furthermore, a combustor tube for guiding combustion gas to a turbine on the downstream side is connected to a swirler support tube provided on the fuel supply side. An annular gap is formed between the swirler supporting cylinder and the combustion cylinder, and a spring clip is arranged in the annular gap. [0004] In the gas turbine combustor configured as described above, the compressed air from the compressor is sucked into the swirler support cylinder. In addition, pa...

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Problems solved by technology

[0012] However, at present, when assembling the combustor, after assembling the combustion tube and the like into the vehicle compartment, the swirler support tube is installed in the vehicle compartment together with the nozzle assembly. And after the swirler support cylinder is installed in the vehicle compartment, the annular gap between the cyclone support cylinder and the combustion cylinder cannot be measured

[0013] On the other hand, in the state where the swirler support cylinder, the combustion cylinder, etc. are assembled and the burner is assembled, there is no measuring device capable of measuring the size of the annular gap between the swirler support cylinder and the combustion cylinder.

[0014] For example, in Patent Documents 1 and 2, there is no description of the measuring device and measuring method for measuring the size of the annular gap between the swirler support cylinder and the combustion cylinder.

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