Gas turbine
There is provided a gas turbine capable of improving the durability of a main shaft by absorbing the deformation of a casing due to heat and pressure and suppressing stresses acting on the main shaft. A link plate 31 of a movable supporting leg 30 that supports a casing 26 of a gas turbine 20 on the turbine 24 side is installed beforehand in an inclined manner at an angle θ 1 , whereby the displacement X of a lower casing 26 L in the height direction; which occurs between a pin 31 a in a top end portion of the link plate 31 and a top surface of a lower casing 26 L when the operation status of the gas turbine 20 shifts from a stop condition to an operating condition is compensated for. This prevents a main shaft 25 from changing in the height direction in the part of the movable supporting leg 30 and suppresses bending stresses acting on the main shaft 25.
1. A gas turbine including a compressor that compresses air, a combustor that supplies a fuel to the air compressed by the compressor and burns the fuel to generate a combustion gas, and a turbine that is rotatably driven by the expansion of the combustion gas generated in the combustor,
wherein a casing forming an outer shell of the gas turbine is supported on a foundation by a first supporting leg that supports the compressor side and a second supporting leg that supports the turbine side,
wherein the first supporting leg supports the casing in a fixed condition with respect to the foundation, and a bias being provided in a seating face of the first supporting leg, and
wherein the second supporting leg supports the casing in a movable condition so as to allow axial and radial deformation and displacement of the casing and is installed beforehand in an inclined manner at a predetermined angle θ to a surface orthogonal to an axis line of the casing when the gas turbine is in a stop condition.
2. The gas turbine according to claim 1 , wherein the second supporting leg is such that top and bottom end portions thereof are rotatably connected to the foundation and the casing by use of pins.
3. The gas turbine according to claim 1 , wherein the second supporting leg is such that the top end portion thereof is connected to the casing in a position below a central axis of the casing.
4. The gas turbine according to claim 3 , wherein the second supporting leg becomes inclined to a direction in which the inclination angle increases further when the operation status of the gas turbine shifts from a stop condition to an operating condition, whereby the second supporting leg absorbs an axial displacement of the casing and a displacement of the height of the central axis of the casing resulting from a temperature change occurring when the operation status of the gas turbine shifts from a stop condition to an operating condition.
5. The gas turbine according to claim 1 , wherein the angle θ is given by θ=tan −1 (ΔH/ΔL) when the axial displacement of the casing on the second supporting leg side resulting from a temperature change occurring when the operation status of the gas turbine shifts from a stop condition to an operating condition is denoted by ΔL and the displacement of the height of the central axis of the casing on the second supporting leg side resulting from the temperature change is denoted by ΔH.