Abstract: A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.

Abstract: A gas turbine has at least one rotor and inner housing part to form an annular chamber therebetween. The annular chamber is fluidically connected to a compressor portion at one end and expansion turbine portion at the other, and is supplied with cooling fluid. First and second swirl supply lines supply the annular chamber with cooling fluid. The cooling fluid is supplied to the surface of the rotor with a tangential flow component, and a first seal element in the annular chamber acts as a flow resistor. A discharge line in the rotor between the first seal element and expansion turbine portion receives and discharges cooling fluid from the second swirl supply line. No bypass lines are provided from the first swirl supply line such that the cooling fluid is conducted around the second swirl supply line in order to be returned to a location of the annular chamber.

Abstract: An insert element fastens to an annular segment body of a turbine of a gas turbine. The annular segment body has a recess on a hot-gas side. The insert element is designed to cover the recess and has a concave front side and a rear side having at least one shaped portion for positioning on the annular segment body. An annular segment has the insert element, a gas turbine has the insert element, and a mounting method mounts the insert element.

Abstract: A gas turbine has at least one rotor and inner housing part to form an annular chamber therebetween. The annular chamber is fluidically connected to a compressor portion at one end and expansion turbine portion at the other, and is supplied with cooling fluid. First and second swirl supply lines supply the annular chamber with cooling fluid. The cooling fluid is supplied to the surface of the rotor with a tangential flow component, and a first seal element in the annular chamber acts as a flow resistor. A discharge line in the rotor between the first seal element and expansion turbine portion receives and discharges cooling fluid from the second swirl supply line. No bypass lines are provided from the first swirl supply line such that the cooling fluid is conducted around the second swirl supply line in order to be returned to a location of the annular chamber.

Abstract: A gas turbine includes a turbine having a rotor blade row and a ring that is arranged around the rotor blade row and is made up of multiple ring segments. An insert element covers a recess of a ring segment body of the turbine. The ring segment body has a recess on a hot-gas side. The insert element has a concavely shaped front face and a rear face with a rear face profile, and the rear face profile corresponds to a negative shape of a profile of the recess. A mounting method includes an insert element fixed to a recess of a ring segment body of a turbine of a gas turbine.

Abstract: A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.

Abstract: An insert element fastens to an annular segment body of a turbine of a gas turbine. The annular segment body has a recess on a hot-gas side. The insert element is designed to cover the recess and has a concave front side and a rear side having at least one shaped portion for positioning on the annular segment body. An annular segment has the insert element, a gas turbine has the insert element, and a mounting method mounts the insert element.

Abstract: A seal assembly (50, 60) for a gas turbine engine for controlling air flow between a diffuser (48) and rotor disks comprising first and second annular flange ends (52, 54) and an annular seal mid-section (56) between and operatively connected to the flange ends (52, 54). The first and second annular flange ends (52, 54) abut respective outer frame members (46) of the diffuser, whereby a fluid flow path is formed between the seal assembly (50, 60) and the rotor disks (42). The first and second end flanges (52, 54) are composed of a material having a coefficient of thermal expansion that is substantially the same as a coefficient of thermal expansion of the material of the outer frame members (46). In addition, the material of the seal mid-section (56) has a coefficient of thermal expansion that is different than that of the materials of the annular flange ends (52, 54) and outer frame members (46).

Abstract: A seal assembly (50, 60) for a gas turbine engine for controlling air flow between a diffuser (48) and rotor disks comprising first and second annular flange ends (52, 54) and an annular seal mid-section (56) between and operatively connected to the flange ends (52, 54). The first and second annular flange ends (52, 54) abut respective outer frame members (46) of the diffuser, whereby a fluid flow path is formed between the seal assembly (50, 60) and the rotor disks (42). The first and second end flanges (52, 54) are composed of a material having a coefficient of thermal expansion that is substantially the same as a coefficient of thermal expansion of the material of the outer frame members (46). In addition, the material of the seal mid-section (56) has a coefficient of thermal expansion that is different than that of the materials of the annular flange ends (52, 54) and outer frame members (46).