Siemens Energy, Inc.

Siemens Aktiengesellschaft

United Technologies Corporation

Florida Turbine Technologies, Inc.

John A Orosa

Yevgeniy P Shteyman

Matthew D Montgomery

Anil L Salunkhe

Lijuan Han

Matthew J Delisa, Iii

Bruce P Biederman

Matthew R Porter

David A Spear

Daniel F Riveros

Robert Anthony Ress, Jr

Joseph D Brostmeyer

Russell B Jones

John E Ryznic

Vincent Paul Laurello

Jose L Rodriguez

Keith D Kimmel

Daniel M Eshak

Ross H Peterson

John Giaimo

Pawel Matys

Ali Akturk

Anthony J Malandra

Marc Samit

David L Wasdell

Jason Kopko

Justin T Cejka

Angelina Hinklein

Dennis N Kantor, Legal Representative

A process for retrofitting an electric power plant that uses two 60 Hertz large frame heavy duty industrial gas turbine engines to drive electric generators and produce electricity, where each of the two industrial engines can produce up to 350 MW of output power. The process replaces the two 350 MW industrial engines with one twin spool industrial gas turbine engine that is capable of producing at least 700 MW of output power. Thus, two prior art industrial engines can be replaced with one industrial engine that can produce power equal to the two prior art industrial engines.

Apparatus and process of retrofitting a combined cycle power plant

An aero gas turbine engine with a fan stage and a bearing rotatably supporting the fan stage, where the bearing is cooled by passing cooling air through the bearing, and the spent bearing cooling air is re-injected into the air flow path at a location where the effect is minimalized. The location is just downstream from a leading edge of a stator vane and along a pressure side surface of the vane. A fine mist of oil can be discharged into the bearing cooling air to also lubricate the bearing, where both the oil and the spent cooling air is reintroduced into the air flow path.

Gas turbine engine fan stage with bearing cooling

A controlled convergence compressor flowpath () configured to better distribute the limited flowpath () convergence within compressors () in turbine engines () is disclosed. The compressor () may have a flowpath () defined by circumferentially extending inner and outer boundaries () that having portions in which the rate of convergence changes to better distribute fluid flow therethrough. The rate of convergence may increase at surfaces () adjacent to roots () of airfoils () and decrease near airfoil tips () and in the axial gaps () between airfoil rows (). In at least one embodiment, the compressor flowpath () between leading and trailing edges () of a first compressor blade () may increase convergence moving downstream to a trailing edge () of the first compressor blade () due to increased convergence of the inner compressor surface (). The compressor flowpath () between leading and trailing edges () of a first compressor vane () immediately downstream from the first compressor blade () may increase convergence moving downstream due to increased convergence of the outer compressor surface ().

Controlled convergence compressor flowpath for a gas turbine engine

A variable pitch fan assembly for an aero gas turbine engine that includes a row of fixed pitch blades in a core stream flow and a row of variable pitch blades in a bypass stream flow, and where a sync ring with a number of hydraulic actuators within a flow splitter of the fan stage is used to vary a pitch of each of the bypass stream flow blades. Hydraulic fluid lines pass through the shaft and through the fixed pitch fan blades into the hydraulic actuators to move the sync ring and vary a pitch of the variable pitch bypass flow fan blades.

Variable pitch fan for gas turbine engine

A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A first flap is arranged diagonally between the tangential strut and the outer cylindrical surface or the inner cylindrical surface where the first flap minimizes vortex shedding of the fluid flow from the tangential strut.

Turbine exhaust cylinder/ turbine exhaust manifold bolted part span turbine exhaust flaps

A process for starting an engine in a cruise missile that is launched from an aircraft during flight, where the cruise missile is ejected from a weapons bay of the aircraft and towed using a tow line, where the cruise missile engine is started while being towed and then released after the engine has started. The tow line is a low radar signature line and the weapons bay door is closed quickly after the cruise missile has been ejected to reduce radar signatures.

Process for launching a cruise missile from an aircraft

An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided.

Turbine exhaust cylinder strut strip for shock induced oscillation control

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

Industrial gas turbine exhaust system with area ruled exhaust path

A gas turbine engine includes inner and outer shrouds forming an annular gas path, and a plurality of struts connecting the inner shroud to the outer shroud. Airfoil shaped shields surround the struts, and each of the shields include a main body having an upstream leading edge defining a chordal axis extending in a downstream axial direction from the leading edge toward a downstream end of the shield. A trailing edge flap is located at the downstream end of each shield, the trailing edge flap including first and second span-wise portions. The first span-wise portion is oriented to direct flow at an angle relative to the chordal axis of the main body and the second span-wise portion is oriented to direct flow in a direction that is at a different angle than the angle of first span-wise portion.

Diffuser with strut-induced vortex mixing

A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade () has an airfoil () uniquely swept so that an endwall shock () of limited radial extent and a passage shock () are coincident and a working medium () flowing through interblade passages () is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point () located at an inner transition radius r-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius r, radially inward of the airfoil tip (), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.

Swept turbomachinery blade

A turbine exhaust diffuser for a gas turbine engine. The diffuser includes a flow ramp positioned on an ID flowpath boundary within a flowpath of the diffuser. The flow ramp extends circumferentially about the hub and includes a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. A wavy portion is located at the downstream, radially outward point of the flow ramp. The wavy portion includes a circumferentially extending, undulating surface defined by alternating axially extending crests and troughs.

Exhaust diffuser including flow mixing ramp for a gas turbine engine

Growing community of inventors

Palm Beach Gardens, FL, United States of America

John A Orosa