Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Anil L Salunkhe

Yevgeniy P Shteyman

John A Orosa

Lijuan Han

Matthew J Delisa, Iii

Matthew R Porter

Daniel F Riveros

Amit K Paspulati

Grzegorz Blaszczak

Dustin C Boudin

Dimitri Zelmer

Krishna Chaitanya Veluru

Sudeep Bosu

Bogdan R Raica

Kashinath Akki

Christian K Funk

Chad W Heinrich

A gas turbine engine having a pre-swirler adjustability is presented. The pre-swirler includes a pre-swirler insert installed in a component enclosed by a cover. The component includes an inner compressor exit diffusor enclosed by an outer casing or a shaft cover enclosed by the inner compressor exit diffusor. The pre-swirler is adjustable by replacing the pre-swirler insert. An access port including an access window is arranged on the cover. The access port gives access to the pre-swirler insert for replacement through the access window. The access window includes a manhole or combustor assembly installation hole on the outer casing, or a cutout on the inner compressor exit diffusor. The access port allows adjusting the pre-swirler by replacing the pre-swirler insert installed in the component without lifting the cover enclosing the component.

Pre-swirler adjustability in gas turbine engine

A mid-frame section of a gas turbine engine having a radial clearance adjustability and a method for adjusting a radial clearance to a rotor in a mid-frame section of a gas turbine engine are presented. The mid-frame section includes a radial clearance adjusting assembly arranged at a compressor exit diffusor. The radial clearance adjusting assembly is configured to adjust the radial clearance to the rotor such that the rotor is concentric with respect to components of the mid-frame section, such as the compressor exit diffusor and shaft cover. The radial clearance adjusting assembly provides radial clearance adjustability in the mid-frame section at multiple locations, such as at forward end and aft end of the compressor exit diffusor. The radial clearance adjusting assembly improves efficiency of the gas turbine and reduces service and operating cost of the gas turbine engine.

Mid-frame section of a gas turbine engine and corresponding method of adjusting radial rotor clearance

A seal assembly in a gas turbine engine is presented. The seal assembly is arranged at a forward side of an inner compressor exit diffusor. The seal assembly is arranged between an outlet guide vane assembly and the forward side of the inner compressor exit diffusor to reduce cooling air leakage therebetween or is arranged between adjacent outlet guide vane assemblies to reduce cooling air leakage therebetween. The seal assembly includes a plurality of seal segments. The seal assembly includes at least one seal, such as a brush seal.

Seal assembly in a gas turbine engine

An exhaust gas diffuser for a gas turbine engine whose inlet geometry can be selectively controlled to change the angular orientation of the diffuser at the location where the exhaust gas exits the last stage row of blades of the turbine section of the gas turbine engine. An end portion of the gas diffuser proximate the last stage row of blades can include one or more actuated sections that are independently controlled to change the angular orientation of the inlet geometry of the diffuser. In one embodiment, the angular orientation of the actuated sections is set at the manufacturing level for the service location of the engine. In another embodiment, the angular orientation of the actuated sections is selectively controlled based on the operating conditions of the engine. In another embodiment, the angular orientation of the actuated sections is controlled by pneumatic pressure from a compressor section of the engine.

High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry

An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Industrial gas turbine exhaust system with splined profile tail cone

Industrial gas turbine exhaust system diffuser inlet lip

Modular industrial gas turbine exhaust system

Industrial gas turbine exhaust system with modular struts and collars

A sealing component () for a turbine () positionable at an interface between a transition section () for carrying exhaust gas and a turbine inlet section (). A U-shaped section () includes first and second legs (). When the sealing component is positioned at the interface, the legs extend about the turbine axis. A seal flange () connects to the U-shaped section. The positioned sealing component extends about the axis and in a direction away from the first leg. The seal flange faces the inner surface () of the flange. A flexible strip (), positioned radially outward with respect to the seal flange, extends about the axis and extends along the axis between the U-shaped section and the flange. The flexible strip acts as a spring member pressing against the outer surface () of the flange.

Flexible component providing sealing connection

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Charlotte, NC, United States of America

Anil L Salunkhe