Siemens Energy, Inc.

Doosan Heavy Industries & Construction Co., Ltd

Mikro Systems, Inc.

Rtx Corporation

Ronald J Rudolph

Ching-Pang Lee

John Joseph Marra

Nan Jiang

Gennadiy Afanasiev

John P Dalton

Jeffrey B Stewart

A turbine blade in an industrial gas turbine includes a blade surface to be cooled by a film of cooling fluid, a plurality of cooling holes on the blade surface through which cooling fluid flows, each cooling hole including an inlet portion and an outlet portion, and a trench on the blade surface surrounding at least one outlet portion of the cooling hole, the trench extending in an axial direction and a radial direction from the outlet portion of the cooling hole, wherein the outlet portion of the cooling hole has a shape configured to generate a first stage diffusion of the cooling fluid and a wall of the trench is positioned in the axial direction from the outlet portion of the cooling hole to generate a second stage diffusion of the cooling fluid, thereby forming the film of cooling fluid.

Enhanced film cooling system

A turbine blade retention system includes a turbine blade including a blade section and a blade platform on which the blade section is attached, the blade platform including a forward angel wing and an aft angel wing, the forward angel wing including a front blade seal groove, a disk configured to receive a plurality of the turbine blades, the disk including a front disk seal groove and an aft disk seal groove, a front seal plate, and an aft seal plate, wherein the front seal plate is slidably connectable to the turbine blade and the disk via the front blade seal groove and the front disk seal groove, and the aft seal plate is removably connectable to the turbine blade and the disk via the aft disk seal groove and a lower wall formed on the aft angel wing.

Turbine blade axial retention and sealing system

A continuous serpentine cooling circuit forming a progression of radial passages (A,A) between pressure and suction side walls () in a MID region of a turbine airfoil (). The circuit progresses first axially, then tangentially, ending in a last radial passage (A) adjacent to the suction side () and not adjacent to the pressure side (). The passages of the axial progression () may be adjacent to both the pressure and suction side walls of the airfoil. The next to last radial passage (A) may be adjacent to the pressure side wall and not adjacent to the suction side wall. The last two radial passages (A,A) may be longer along the pressure and suction side walls respectively than they are in a width direction, providing increased direct cooling surface area on the interiors of these hot walls.

Integrated axial and tangential serpentine cooling circuit in a turbine airfoil

Multi-scale turbulation features, including first turbulators () on a cooling surface (), and smaller turbulators () on the first turbulators. The first turbulators may be formed between larger turbulators (). The first turbulators may be alternating ridges () and valleys (). The smaller turbulators may be concave surface features such as dimples () and grooves (), and/or convex surface features such as bumps () and smaller ridges (). An embodiment with convex turbulators () in the valleys () and concave turbulators () on the ridges () increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.

Compound cooling flow turbulator for turbine component

A seal assembly for an axial flow gas turbine engine includes a rotatable component having a radially extending mate face, a seal slot formed in the mate face, and a seal member slidably disposed in the seal slot. The seal slot includes a radially outer wall and an opposing radially inner wall extending into the component in a circumferential direction from the mate face. The radially outer wall is angled radially inwardly from the mate face toward an inner end portion of the seal slot. Rotation of the seal assembly during operation of the engine produces a centrifugal force on the seal member to effect movement of the seal member in the circumferential direction out of the seal slot.

Growing community of inventors

Miami, FL, United States of America

Ronald J Rudolph