TURBOMACHINE

A turbomachine is provided. The turbomachine includes a casing, a first airfoil disposed inside the casing such that a fluid passes through the first airfoil while flowing through the casing, a first inner frame coupled to a radially inner end of the first airfoil, a first inner wing protruding from the first inner frame in an axial direction of the casing, a second airfoil disposed inside the casing and between adjacent first airfoils in a flow direction of a fluid, a second inner frame coupled to a radially inner end of the second airfoil and disposed adjacent to the first inner frame, a second inner wing protruding from the second inner frame along the axial direction of the casing and disposed adjacent to the first inner wing, and a plurality of rim seals disposed between the first inner wing and the second inner wing, arranged at intervals along a circumferential direction of the casing, and configured such that cooling air present inside the first and second inner wings in a radial direction flows into each rim seal through an ingress port, passes through each rim seal, and flows out through an egress port, wherein a region on a downstream side of the first airfoil in the flow direction of the fluid flowing through the casing is divided into a first region having a relatively high pressure and a second region having a relatively low pressure, a first flow passage and a second flow passage are provided in a gap between each rim seal, the first flow passage is configured such that a size in the circumferential direction increases from the ingress port to the egress port and the egress port communicates with the first region, and the second flow passage is configured such that a size in the circumferential direction decreases from the ingress port to the egress port and the egress port communicates with the second region.