A vane segment for a gas turbine engine according to an exemplary aspect of the present disclosure includes an inner vane platform relative an axis, the inner vane platform having a non-axisymmetric surface contour.

Gas turbine engine with non-axisymmetric surface contoured vane platform

A gas turbine and a seal (108, 904) assembly (101) for a machine (100) having a rotating shaft (106), a wheel (104) coupled to the rotating shaft (106), the wheel (104) including a bucket (102) coupled to the wheel (104) comprising a coverplate (110) that is fastened to the wheel (104) and the bucket (102) and a seal (108, 904) positioned between the coverplate (110) and the wheel (104) and the bucket (102).

Gas turbine having seal assembly with coverplate and seal

A gas turbine engine component comprises a frame and a fairing. The frame comprises a monolithic ring-strut-ring structure. The fairing comprises a multi-segment ring-strut-ring structure that is assembled around the frame. A method of assembling the frame and fairing comprises positioning a plurality of shroud segments within a frame and joining the plurality of shroud segments to each other so that the fairing is trapped within the frame. In one embodiment, the fairing comprises a plurality of outer diameter shroud segments, a plurality of inner diameter shroud segments, a plurality of strut segments, and stiffening features connected to the plurality of strut segments to strengthen the fairing.

Multi-piece fairing for monolithic turbine exhaust case

A combustion chamber (20) of a combustor (16) for a gas turbine (10) is presented. A combustion chamber (20) includes a plurality of segments arranged annularly about an axis of the combustion chamber (20), each segment comprising a radial inner wall portion (54) and a radial outer wall portion (56), a first section (62) comprising an opening (63) for the installation of a burner (17), and a second section (64) at which at least one airfoil (52) extends between the radial inner wall portion (54) and radial outer wall portion (56) of the segment.

Combustion chamber of a combustor for a gas turbine

The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing.

Guide vane of a gas turbine and method for replacing a cover plate of a guide vane of a gas turbine

Gas turbine (1) with at least two combustion chambers and a turbine, in which guide vanes (14), which are arranged in a ring respectively with a base body of the blade (28) are arranged , covering each base body of the blade (28) having a blade root (18), a cover plate (26) and a blade airfoil (24) profiled extending therebetween, being attached on each of the bodies blade root (28) a guide body flow (30) with a front deflector blade (32), which is connected ahead of the blade leaf (24) relative to the flow direction of the working medium (M) of the gas turbine (1), characterized in that at least two vanes (14) of the crown of vanes have flow guide bodies (30) with different advance guide blades (32)

Guide vane for a gas turbine.

The insert has a throttle plate (B) with passages (D) whose dimensions determine the throttle performance of a coolant stream between compartments. Flexible sealing elements are designed as metal wools (A) that are sealably attached at edge regions of the throttle plate. Airfoil-shaped blade walls (W1, W2) form a hollow chamber for guiding a coolant stream, where the hollow chamber is bound by the blade walls of a turbine blade. Guiding elements (S1, S2) are designed in a manner such that the insert is tightly attached via the flexible sealing elements. An independent claim is also included for a turbine blade for a gas turbine.

Metering insert for turbine blade and corresponding turbine blade

An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine.

Axial turbine for a gas turbine with limited play between blades and housing

The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.

Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine

A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.

Thorsten Mattheis

Papers

Guide vane for a gas turbine.

Metering insert for turbine blade and corresponding turbine blade

Axial turbine for a gas turbine with limited play between blades and housing

Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine

Gas turbine with a guide vane