Clearance control schemes for controlling a clearance defined between a first component and a second component of a gas turbine engine are provided. In one aspect, an engine controller of the gas turbine engine implements a clearance control scheme, which includes receiving data indicating a clearance between the first component and the second component, the clearance being at least one of a measured clearance captured by a sensor and a predicted clearance specific to the gas turbine engine at that point in time; comparing the clearance to an allowable clearance; determining a clearance setpoint for a clearance adjustment system based on a clearance difference determined by comparing the clearance to the allowable clearance; and causing the clearance adjustment system to adjust the clearance to the allowable clearance based on the clearance setpoint.

A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (Δr) along the radial direction, a total volume (V), and a normalized radius (r′). The normalized radius (r′) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation:

[00001]$0.1{\left(r^{\prime }\right)}^{-1}<\frac{\text{Δ}r}{r}<\text{K}{\left(r^{\prime }\right)}^{-4/3}.$

wherein the normalized radius (r′) is between 1.25 and 8 and K is equal to 40%, or the normalized radius (r′) is between 2.75 and 4.5 and K is equal to 65%.

A power plant with a water-steam-cycle includes a steam generator with a plurality of heating surfaces that carry a fluid and transfer heat to the fluid. The plurality of heating surfaces has an economizer for preheating the fluid and a fluidly connected evaporator for producing steam. A steam turbine receives the steam produced in the steam generator to generate power output. A condenser condenses steam from the steam turbine. The condenser has a hotwell as collection container for condensed steam or water. A polishing plant is arranged fluidly between the hotwell of the condenser and the economizer. A drain line interconnects an outlet of the economizer and the hotwell of the condenser. A fluid line interconnects the outlet of the economizer and the evaporator. The fluid line includes a syphon to hold back water in the economizer.

A gas turbine engine has a fan case exit and an inner core housing exit. At least one of the exits is provided with a fiber optic sensing unit. The fiber optic sensing unit includes a fiber optic sensing member surrounding a circumference of the at least one of the exits. A control is programmed to calculate a nozzle area at the at least one of the exits based upon the displacement of the fiber optic sensing member. The calculated nozzle area is utilized to update nozzle area information at an electronic engine controller for the engine, and the electronic engine controller is programmed to control at least one associated component on a gas turbine engine based upon the updated nozzle area. A method is also disclosed.

Systems and methods to control gas turbine firing temperatures during air injection. A method of achieving a desired firing temperature of a gas turbine engine during air injection comprises injecting compressed air into the gas turbine engine using an external source. The external source includes a compressor and a recuperator. The method comprises using a controller of the gas turbine engine to: (a) determine an air injection exhaust bias gain using an inlet temperature of the gas turbine engine; (b) calculate, based on the determined air injection exhaust bias gain and a flow rate of the injected compressed air, an air injection exhaust curve bias; and (c) change a fuel flow of the gas turbine engine by adding the air injection exhaust curve bias to an existing exhaust curve of the gas turbine engine to thereby achieve the desired firing temperature during air injection.

Impeller for a radial fan, the impeller comprising a front side, a rear side and a peripheral edge, a hub element, an annular covering disc positioned on the front side, an intake opening formed on the front side, a support disc positioned on the rear side, blades extending substantially radially from the hub element towards the peripheral edge, and outflow openings formed in the region of the peripheral edge. A first outer diameter of a radially outer edge of the annular covering disc is greater than a second outer diameter of a radially outer edge of the support disc. Openings are formed in the annular covering disc, wherein the openings are positioned between the radially outer edge of the annular covering disc having the first outer diameter and a radially inner edge of the annular covering disc having a first inside diameter.

Turbines and associated equipment are normally cleaned via water or chemical pressure washing via a mist, spray systems. However, these systems fail to reach deep across the gas path to remove fouling materials. Various embodiments herein pertain to apparatus and methods that utilize the water and existing chemicals to generate a foam. The foam can be introduced at that gas-path entrance of the equipment, where it contacts the stages and internal surfaces, to contact, scrub, carry, and remove fouling away from equipment to restore performance.

A starter air valve (SAV) system can include a pressure actuated SAV actuator configured to be operatively connected to a SAV and a first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator. The first pressure valve can be a pulse-width modulation solenoid valve configured to provide a duty cycle of pressure from the pressure source to the SAV actuator.

The present invention discloses a novel modular system and methods of operating an increased air supply to a gas turbine engine such that the upon supplying a source of external air to the system, a bias is added to the exhaust temperature such that a firing temperature with air injection is substantially equivalent to the firing temperature without air injection.

A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.