Gas turbine
The present invention includes a flow guide ( 17 ) that is disposed in a space ( 15 A) formed in a casing, on an outlet side of a diffuser ( 14 ), the flow guide including: a first guide surface ( 17 a ) that is disposed on a rotor side provided to a compressor and a gas turbine, and that delays turning of a flow direction of a compressed gas which has passed through the diffuser ( 14 ); and a second guide surface ( 17 b ) that is disposed outside the first guide surface ( 17 a ) and that turns the flow direction of the compressed gas which has passed through the diffuser ( 14 ).
1. A gas turbine comprising:
a compressor which compresses gas to generate a compressed gas;
a casing in which a space is formed;
a combustor which is disposed in the space of the casing and generates a combustion gas using the compressed gas;
a turbine which is provided downstream from the combustor and is driven by the combustion gas;
a diffuser which connects an outlet of the compressor and an entrance of the casing, is gradually enlarged in diameter from the outlet of the compressor toward the entrance of the casing, and defines a flow path that guides the compressed gas to the space;
a flow guide provided on an outlet side of the diffuser in the space formed in the casing; and
a rotor disposed from the compressor to the turbine,
wherein the flow guide has an annular shape, and includes:
a first guide surface which is provided on a rotor side and delays turning of a flow direction of the compressed gas that has passed through the diffuser; and
a second guide surface which is disposed outside the first guide surface and turns the flow direction of the compressed gas that has passed through the diffuser,
wherein the first guide surface is inclined in a direction approaching an axis of the rotor from the leading edge toward a trailing edge of the flow guide, and
wherein a leading edge of the flow guide is disposed downstream from an outlet of the diffuser or the leading edge of the flow guide is disposed at a position which coincides with the outlet of the diffuser.
2. The gas turbine according to claim 1 , wherein the second guide surface is a curved surface which curves in a direction going away from the axis of the rotor from the leading edge toward the trailing edge of the flow guide.
3. The gas turbine according to claim 1 ,
wherein the diffuser includes a first tubular portion, and a second tubular portion which is disposed outside the first tubular portion and the flow path is defined between the first tubular portion and the second tubular portion, and
a plurality of struts, which connect the first tubular portion and the second tubular portion in a radial direction of the rotor, are disposed in a circumferential direction of the rotor, and support the flow guide.
4. The gas turbine according to claim 3 , wherein shapes of the plurality of struts are blade shapes.
5. The gas turbine according to claim 3 ,
wherein the plurality of struts are disposed so as to partially overlap the combustor in the circumferential direction of the rotor, and
inner sides of leading edge portions of the plurality of struts are inclined to form acute angles with respect to the axis of the rotor.
6. The gas turbine according to claim 3 ,
wherein the first tubular portion includes an outer circumferential surface facing the second tubular portion,
the second tubular portion includes an inner circumferential surface facing the first tubular portion, and
a first angle formed by the axis of the rotor and the outer circumferential surface is smaller than a second angle formed by the axis of the rotor and the inner circumferential surface.