General Electric Company

Ge Avio S.r.l.

Bhaskar Nanda Mondal

Pranav R Kamat

Jeffrey Donald Clements

Thomas Ory Moniz

Narayanan Payyoor

Atanu Saha

Jeffrey Douglas Rambo

Christopher Charles Glynn

David William Crall

Tsuguji Nakano

Peeyush Pankaj

Arnab Sen

Veeraraju Vanapalli

Vinod Shashikant Chaudhari

Vaishnav Raghuvaran

Vaibhav M Deshmukh

Brandon Wayne Miller

Darek Tomasz Zatorski

Richard Ludwig Schmidt

Rajesh Kumar

Shashank Suresh Puranik

Sushilkumar Shevakari

Robert Proctor

Scott Hunter

Christopher James Kroger

Steven Alan Ross

Ramana Reddy Kollam

Joel Francis Kirk

John Joseph Rahaim

Trevor Wayne Goerig

Daniel Fusinato

Sanjeev Sai Kumar Manepalli

Kishanjit Pal

Rakshit Tirumala

Arthur William Sibbach

Alan Roy Stuart

Karthikeyan Sampath

Kenneth Edward Seitzer

Gary W Bryant

Hemanth Gudibande Sathyakumar Kumar

Sushilkumar Gulabrao Shevakari

Arda Unsal

Jagata Laxmi Narasimharao

Nicholas Joseph Kray

Ravindra Shankar Ganiger

Daniel Alan Niergarth

Trevor Howard Wood

Kishore Ramakrishnan

Nitesh Jain

Steven Douglas Johnson

Apostolos Pavlos Karafillis

Ian Francis Prentice

Changjie Sun

Praveen Sharma

Nathan Evan McCurdy Gibson

Craig William Higgins

Monty Lee Shelton

Gary Willard Bryant, Jr

Curtis Walton Stover

Wenfeng Lu

Joseph George Rose

Sesha Subramanian

Viswanadha Gupta Sakala

Bruce Alan Carter

Rajendra Mahadeorao Wankhade

Arvind Namadevan

Kevin Lee Kirkeng

Antonio Giuseppe D'Ettole

Jacob Patrick Miller

Shankar Jayaraman

Marcia Boyle Johnson

Mayank Krisna Amble

Keith Blodgett

Randy Thomas Antelo

Shishir Paresh Shah

Mohamed Musthafa Thoppil

Yu Mukherjee

Sivakumar Mahesh

Ramesh Balla

Anil Soni

Subramanian Narayanan

Andrew Mark Del Donno

Durga Srinivas Chillapalli

Vaibhav Deshmukh M

N V Sai Krishna Emani

Ranganayakulu Alapati

A turbomachine engine includes an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine. The engine core has a length (L), and the high-pressure compressor has an exit stage diameter (D). A high-pressure shaft is coupled to the high-pressure compressor and the high-pressure turbine. The high-pressure shaft is characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and a ratio of L/Dis from 2.1 to 4.3.

High-speed shaft rating for turbine engines

A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.

Passive control of gas turbine clearances using ceramic matrix composites inserts

A turbine engine for an aircraft including a turbo-engine, a fan having a fan shaft coupled to the turbo-engine, and a steam system. The steam system is fluidly coupled to a core air flow path at a plurality of steam injection locations to selectively inject steam into the core air flow path at each of the plurality of steam injection locations, using a steam flow control valve. The plurality of steam injection locations include (i) an upstream steam injection location located to inject steam into the core air flow path at a primary combustion zone of a combustor or upstream thereof and (ii) a downstream steam injection location located to inject steam into the core air flow path downstream of the primary combustion zone.

Turbine engine including a steam system

A turbine engine includes a spool with a compressor for providing a compressed air flow to a turbine, a shaft that connects the compressor and a turbine such that the compressor and the turbine rotate together, and a fuel supply. A combustor located downstream of the compressor receives and combusts the compressed air flow and the fuel supply, generating combustion gases. The combustion gases rotate the turbine, in turn rotating the spool. A balance piston for applying an axial force on the spool includes a rotating boundary portion and a fixed enclosure portion that does not rotate, defining a balance piston cavity. A water system provides water to the balance piston cavity, heat transfer from the balance piston to the water causes expansion of the water, the water in the balance piston cavity being balance piston fluid that is pressurized and applies an axial force to the spool.

Turbine engine including a water system

A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes four rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 2.0-5.1. Additionally (or alternatively) the low-pressure turbine includes an area-EGT ratio within a range of 1.05-1.6.

Turbomachinery engines with high-speed low-pressure turbines

A fan assembly for an engine includes a fan disk, fan disk inserts, and fan blades. The fan disk includes disk posts extending in a radial direction from a central region of the fan disk. The disk posts include disk post pressure surfaces that define a first array of dovetail recesses. The fan disk inserts are retained within the first array of dovetail recesses. The fan disk inserts include fan disk insert pressure surfaces that define a second array of dovetail recesses. The fan blades are retained within the second array of dovetail recesses.

Fan assemblies with fan disk inserts and methods of assembling the same

A turbine engine includes a cooling air duct for cooling air positioned radially between a core air flow path for core air and a bypass airflow passage for bypass air. A heat exchanger is positioned in the cooling air duct to transfer heat from a heat source from within the turbine engine. The heat exchanger may be a condenser. The turbine engine may further include a steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flow path, the steam system including the condenser to transfer heat from the combustion gases to the cooling air and to condense the water from the combustion gases. The turbine engine may further include a booster fan to increase the pressure of the cooling air and the core air.

Turbine engine with three air streams

A fan assembly includes a disk having a disk forward surface, a disk aft surface, and a radially outer surface. The disk defines a plurality of disk posts and a plurality of disk slots in the radially outer surface. At least one of the plurality of disk posts includes a post slot. The fan assembly also includes a fan having a plurality of fan blades and a plurality of platforms extending between adjacent fan blades of the plurality of fan blades. Each of the plurality of fan blades is received within one of the plurality of disk slots via a respective blade root. Further, the fan assembly includes at least one fan retention member having a body portion and a protrusion extending from the body portion. The protrusion is received within the post slot such that the at least one fan retention member supports one of the plurality of platforms.

Fan retention member for supporting a blade platform of a fan assembly

A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.

Counter-rotating gas turbine engines including turbine sections with separable torque frames

Structures for reducing forward loads in compressors are described. A compressor includes inner and outer circumferential support structures positioned concentrically around a central axis, and an aft-most stage including a vane extending radially inward from the outer circumferential support structure. An axial length of the aft-most stage is defined by a spacer arm of the inner circumferential support structure. The vane includes a root, a tip, and a trailing edge extending between the root and the tip. A ratio of a first radial distance between a first point located at an intersection of the tip of the vane and the trailing edge to a radially inner wall of the spacer arm of the inner circumferential support structure to a second radial distance between the first point and a second point located at an intersection of the root of the vane and the trailing edge is between 0.95 and 4.5.

Forward load reduction structures for aft-most stages of high pressure compressors

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Bengaluru, India

Bhaskar Nanda Mondal