Abstract: The invention concerns a gas turbine having a picture frame, a first vane, and a sealing arrangement to seal a gap between the picture frame and the first vane, the sealing arrangement including two seals arranged in series between the picture frame and the first vane. In exemplary embodiments, one of the seals is a honeycomb seal, a dogbone seal, a hula seal or a piston seal and the other seal is a honeycomb seal, a dogbone seal, a hula seal or a piston seal. A method of supplying cooling fluid to the gap between the picture frame and the first vane is also disclosed.

Abstract: A first stage vane arrangement having an array of first stage vanes and an array of frame segments and method for cooling frame segments of the first vane arrangement of a gas turbine are disclosed. The frame segments are designed for axially receiving aft ends of a combustor transition pieces. The first stage vanes include extended vanes, each vane having a leading section, a trailing edge, and an airfoil extending between an outer platform and an inner platform. The frame segments having an I-beam with an upper horizontal element, a lower horizontal element, and a vertical web. The vertical web having a downstream face facing towards a first stage of a turbine when installed in a gas turbine. The downstream face of the vertical web of at least one of the frame segments overlaps, at least partially, the leading section of at least one of the extended vanes.

Abstract: The disclosure relates Frame segment for a transition piece-turbine interface having a picture frame receptacle for axially receiving an aft end of a combustor transition piece. The frame segment can include an I-beam with an upper horizontal element, a lower horizontal element, and a vertical web, wherein the upper horizontal element has mounting face for fixation to a vane carrier. The vertical web has a downstream face, facing towards a first stage of a turbine when installed in a gas turbine. The vertical web includes a cooling gas duct for supplying cooling gas to the downstream face of the vertical web.

Abstract: The disclosure relates to a vane arrangement with a vane carrier, an array of rocking first stage vanes, and an array of frame segments for axially receiving aft ends of a combustor transition pieces. The frame segments comprise an I-beam with an upper horizontal element, a lower horizontal element, a vertical web, a radially outer fixation to the vane carrier, and an arm extending from the lower horizontal element in axial direction below the inner rim segment for supporting the inner platform of the vane and for sealing a gap between the inner platform and the lower horizontal element. Besides the vane arrangement the disclosure relates to a method for assembly of such an arrangement as well as to a gas turbine comprising such a vane arrangement.

Abstract: A first stage vane arrangement having an array of first stage vanes and an array of frame segments and method for cooling frame segments of the first vane arrangement of a gas turbine are disclosed. The frame segments are designed for axially receiving aft ends of a combustor transition pieces. The first stage vanes include extended vanes, each vane having a leading section, a trailing edge, and an airfoil extending between an outer platform and an inner platform. The frame segments having an I-beam with an upper horizontal element, a lower horizontal element, and a vertical web. The vertical web having a downstream face facing towards a first stage of a turbine when installed in a gas turbine. The downstream face of the vertical web of at least one of the frame segments at least partially, the leading section of at least one of the extended vanes.

Abstract: The invention concerns a gas turbine having a picture frame, a first vane, and a sealing arrangement to seal a gap between the picture frame and the first vane, the sealing arrangement including two seals arranged in series between the picture frame and the first vane. In exemplary embodiments, one of the seals is a honeycomb seal, a dogbone seal, a hula seal or a piston seal and the other seal is a honeycomb seal, a dogbone seal, a hula seal or a piston seal. A method of supplying cooling fluid to the gap between the picture frame and the first vane is also disclosed.

Abstract: The disclosure relates Frame segment for a transition piece-turbine interface having a picture frame receptacle for axially receiving an aft end of a combustor transition piece. The frame segment can include an I-beam with an upper horizontal element, a lower horizontal element, and a vertical web, wherein the upper horizontal element has mounting face for fixation to a vane carrier. The vertical web has a downstream face, facing towards a first stage of a turbine when installed in a gas turbine. The vertical web includes a cooling gas duct for supplying cooling gas to the downstream face of the vertical web.

Abstract: The disclosure relates to a vane arrangement with a vane carrier, an array of rocking first stage vanes, and an array of frame segments for axially receiving aft ends of a combustor transition pieces. The frame segments comprise an I-beam with an upper horizontal element, a lower horizontal element, a vertical web, a radially outer fixation to the vane carrier, and an arm extending from the lower horizontal element in axial direction below the inner rim segment for supporting the inner platform of the vane and for sealing a gap between the inner platform and the lower horizontal element. Besides the vane arrangement the disclosure relates to a method for assembly of such an arrangement as well as to a gas turbine comprising such a vane arrangement.