General Electric Company

United Technologies Corporation

Steven Mark Schirle

Michael James Dutka

John David Stampfli

Joseph Anthony Cotroneo

David Allen Eldredge

Syed J Khalid

Carl Gerard Schott

Philip Lynn Andrew

Paul Griffin DeIvernois

Nicholas Francis Martin

Steven Eric Tomberg

Gary M Perkins

Sanjay Bharadwaj

John Franklin Ryman

Narayanan Venkateswaran

Peter Gaines Cleveland

Nathan Stafford Race

Nick Martin

Ronald Stuart Denmark

William John Miller

Samy Baghdadi

Christopher David McGowan

Timothy Edward DeJoris

Chung-Hei Yeung

Chung-hei Simon Yeung

Venkata Siva P Chaluvadi

Chad J Yetka

Jennifer B Michenfelder

Timothy E Dejoris

Roger Claude Beharrysingh

Adrian Mircea Mistreanu

Jeffrey Boyd

Jason Thomas Harrell

Anthony Donnaruma

Johnalagadda Venkata Rama Prasad

Jonnalagadda Venkata Rama (jvr) Prasad

Chung-hei (Simon) Yeung

James Michael Hill

Timothy Dejoris

A method of starting up a turbine with a compressor have an inlet guide vane, a number of bleed valves, and a number of blades so as to limit the duration in a rotating stall window. The method may include starting rotation of the blades, increasing the speed of the rotation of the blades, closing one or more bleed valves so as to shift the rotating stall window to a higher rotational speed, partially opening the inlet guide vane to a position outside the rotating stall window, and opening the bleed valves while partially closing the inlet guide vane such that the number of blades pass through the rotating stall window.

Turbine anti-rotating stall schedule

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S&#x2013;16S, 1R&#x2013;17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Air foil shape for a compressor blade

Aerodynamically efficient air flow management in axial flow-turbines is provided by utilizing a variable stagger and camber airfoil. In an exemplary embodiment of the invention, this is accomplished by providing a two-piece airfoil including a strut and a flap, each of which is mounted to articulate about a common, radially oriented axis. The strut and flap are respectively positioned by a strut gear and a flap gear, located at the radial end of the airfoil and, in an exemplary embodiment, are driven by a stepped synchronizing ring.

Variable camber and stagger airfoil and method

An blade row for use in a compressor is provided. The blade row has a plurality of inlet guide vanes. Each inlet guide vane has a meanline approximately equal to NACA standard A4K6 meanline, a thickness distribution approximately equal to NACA standard SR 63 thickness distribution, a stagger angle, and a lift coefficient between 0.0 and 0.8.

Inlet guide vane for axial compressor

An apparatus for monitoring the health of a compressor having at least one sensor operatively coupled to the compressor for monitoring at least one compressor parameter, a processor system embodying a stall precursor detection algorithm, the processor system operatively coupled to the at least one sensor, the processor system computing stall precursors. A comparator is provided to compare the stall precursors with predetermined baseline data, and a controller operatively coupled to the comparator initiates corrective actions to prevent a compressor surge and stall if the stall precursors deviate from the baseline data, the baseline data representing predetermined level of compressor operability.

Method and apparatus for continuous prediction, monitoring and control of compressor health via detection of precursors to rotating stall and surge

An apparatus for monitoring the health of a compressor including at least one sensor operatively coupled to measure the dynamic pressure of gases flowing through the compressor, a processing system coupled to at least one sensor, the processor system recording and processing the measurements made by at least one sensor. The apparatus further includes a comparator that compares the sensor measurements with predetermined baseline values, and a real-time controller coupled to the comparator, the controller initiating corrective actions to prevent a compressor surge if the sensor measurements deviate from the predetermined baseline values.

Method and apparatus for compressor control and operation in industrial gas turbines using stall precursors

A method is disclosed for monitoring and controlling a compressor including (a) monitoring at least one compressor parameter; (b) storing data indicative of the monitored parameter in a database system; (c) processing the collected data using a stall precursor detection algorithm to determine a stall precursor; (d) comparing the stall precursor with at least one of a corresponding average compressor value, and a corresponding unit specific value to determine the level of compressor operability, and (e) if the stall precursor varies from at least one of the average compressor value and the unit specific value, performing corrective actions to vary the level of compressor operability to prevent a surge condition.

Method and apparatus for detecting and compensating for compressor surge in a gas turbine using remote monitoring and diagnostics

The end wall of the compressor adjacent the stator vanes and compressor blades is configured so that the annular region between the vanes and blades is held at a constant area and that the flow path convergence of the stator is increased to compensate for the loss of convergence due to the reduction of convergence in the annular region between vanes and blades.

End wall flow path of a compressor

A variable cycle gas turbine engine (10) includes a core unit (30) having a guide vane array (36), and a hybrid stage (38) with a rotor blade array (40) and a stator vane array (42). The engine is operable in at least two modes which channel different quantities of working medium air to the core unit, and each mode corresponds to a distinct thermodynamic cycle. The vanes (54) of the hybrid stage stator vane array are bivariable so that the leading segment (140) and trailing segment (146) of each vane are separately adjustable over a range of pitch angles. The bivariable character of the vanes ensures aerodynamic stability of the engine in each of its modes of operation.

Variable cycle engine with enhanced stability

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Anderson, SC, United States of America

Steven Mark Schirle