Abstract: A temperature measuring system is disclosed herein. The temperature measuring system includes an optical assembly and a spectral data receiver. The temperature measuring system views passing gas and measures the radiant response of a selected gas. The measurement includes radiant intensities with respect to wavelengths in the infrared region.

Abstract: During operation, a bladed rotor disk typically experiences out-of-plane vibration which can result in deterioration and/or cracking at the interface between adjacent shrouds of the turbine blades. In an embodiment, slots are formed at the end of a labyrinth seal segment of each shroud. Preloaded spring strips are inserted through the slots to couple adjacent shrouds while preventing the natural frequency of the turbine blades from drifting to the operating speed range and/or providing vibration damping to the untuned blade mode.

Abstract: A thermal bridge forms a connection between a cold side and a hot side that is capable of withstanding a large temperature differential while high-pressure gas (e.g., air) flows between the two sides within an internal passageway. A cold-side region and hot-side region of the thermal bridge may each have a flange with a plurality of holes. The cold-side region may also include a conical fillet with counterbore recesses to provide access to each of the plurality of holes from a low radial position.

Abstract: A damped turbine blade assembly for a gas turbine engine is disclosed. The damped turbine blade assembly includes a damper positioned within a first small slot of a first turbine blade and a second large slot of the second turbine blade. A portion of the damper can slidably mate with the second large slot providing a radial and angular connection between the first turbine blade and second turbine blade while allowing movement in a direction tangent to a radial of a center axis of the gas turbine engine. The tangential movement is resisted by friction between the damper contacting the second large slot and provides friction damping against vibrations felt by the turbine blades during operation of the gas turbine engine. The damper can be shaped and/or pre-stressed to control the normal force component of the friction between the damper and the second large slot.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel stem assembly for receiving and distributing fuel and an injector head receiving fuel from the fuel stem assembly. The injector head can include an injector body, swirler vanes, a pilot assembly, passages, and fuel galleries. The pilot assembly can include pilot struts and a pilot tube. The swirler vanes and pilot struts can include passages to transport the pilot fuel from the fuel stem assembly to the pilot tube.

Abstract: A control system for a gas turbine engine is disclosed. In embodiments, control system includes a controller and a high speed recorder. The controller obtains a sensor value from a sensor connected to the gas turbine engine and publishes a tag that includes the type of event, the sensor value, and a timestamp. The high speed recorder checks the tag for an overspeed event. If an overspeed event is detected, the high speed recorder records values provided by the tag.

Abstract: A contamination sensor for a gas turbine engine is disclosed herein. The contamination sensor is made of a selected composition of material and includes a base alloy, an alloy for improving oxide formation, and at least one element from the transition metal group. The composition of the contamination sensor can be adjusted to react with specific contaminants at specific temperature ranges.

Abstract: Systems and methods for improved gas turbine engine performance are disclosed. The method can include receiving an error function for a wide range of fuels. The error function can provide lower heating value (LHV) corrections over the wide range of fuels. The method can include receiving gas turbine engine operation data for a first period of run time on the gas turbine from one or more sensors of the gas turbine engine. The engine operation data can include a performance data points. The method can include determining an optimum LHV based on the engine operation data for the first period of run time and the error function. The method can then include adjusting fuel consumption of the gas turbine engine based on the optimum LHV.

Abstract: A pressure capture canister is disclosed. The pressure capture canister includes a body, a cap, and a seal. The cap and the seal are positioned within the body and are arranged to allow fluid communication from outside of the pressure capture canister to within the body. The seal can be selected to melt or soften at a temperature threshold.

Abstract: An integrated gas compressor is disclosed herein. The integrated gas compressor includes an integrated motor with a stator, centrifugal impellers, and a shaft assembly with a rotor and conical transition. The integrated motor can produce an electromotive force that is imparted by the stator to rotate the rotor and components coupled to the rotor, such as the conical transition and the centrifugal impellers. At least one of the rotor and conical transition have a cavity.

Abstract: A method and control system for controlling compressor output for a gas turbine engine is disclosed. The power output of a gas turbine engine can vary and be below desired output levels due to operating conditions such as ambient temperature and elevation. These operating conditions can lead to lower output of the gas compressor of the turbine engine and lower operating temperatures within or proximate to a turbine of the gas turbine engine and lead to less power output. Additional fuel can be added to increase power to the gas producer shaft and increase turbine temperature of the gas turbine engine. A power transfer device can be used to remove or add power to the gas producer shaft to balance the gas producer mechanical limits and turbine thermal limits at maximum levels and lead to higher power output.

Abstract: Systems and methods for providing an automatic fuel polishing and on-demand fuel delivery for one or more gas turbine engine test cells are provided. The system can have a polishing loop that can continuously polish fuel. The polishing loop can have at least a fuel storage tank, a pump assembly, a filtration system, and a flow meter. The system can also have fuel delivery path coupled to the polishing loop at a three way junction. The three way junction can enable the continuous polishing loop when no test cells are operating. Upon initiation of one or more test cells, the delivery path can draw fuel from the polishing loop via the three way junction for use by the test cells. The flow meter can measure a corresponding drop in flow within the polishing loop and cause an increase in flow by the pump assembly.

Abstract: A system and method for resource estimation of an additive manufacturing device is disclosed herein. The system includes at least one processor and one or more software modules. The processor executes the one or more software modules to determine a number of parts that can be manufactured per manufacturing run, estimate manufacturing time to manufacture a specified number of parts, and determine a total cost to manufacture the number of parts with the additive manufacturing device. The one or more software modules can compare the total cost to the cost of a current manufacturing method.

Abstract: This disclosure provides an air tube for a combustor of a gas turbine engine. The air tube includes an inner tube and an outer tube to deliver discharged compressor air into a combustion chamber of the combustor. The air tube can include struts and fins that can improve the cooling performance of the air tube during operation of the gas turbine engine.

Abstract: A magnetic bearing assembly for a rotary machine may lose power and fail to support the rotating assembly resulting in damage to magnetic bearing assembly and/or other components. An auxiliary bearing assembly may be used to support the rotating assembly during such a failure. The auxiliary bearing assembly is located radially inwards of the magnetic bearing assembly and may reduce resonance and/or whirl of the rotating assembly during failure of the magnetic bearing assembly.

Abstract: A fuel delivery system having a base, a fuel inlet configured to receive fuel from a secondary fuel supply, a fuel outlet configured to deliver fuel to a machine, a filter assembly and a coalescer configured to filter the fuel, a fuel controller configured to regulate pressure of the fuel that will be delivered to a machine, a boost pump assembly and a main pump assembly configured to pressurize the fuel.

Abstract: This disclosure provides a tube shaping tool for a torque mechanism to modify a tube end. The tube shaping tool can include a cup and an internal assembly. The internal tube assembly can include a stem and an internal body. The stem can be received by the torque mechanism and transmit torque generated from the torque mechanism to the components of the tube shaping tool. The tube shaping tool can roll form the outside diameter of the tube end using standard bearings and a flange bearing attached to the internal body. The flange bearing can also include a flange that can provide facing of the tube end.

Abstract: A turbine blade having a base and an airfoil, the base including cooling air inlets and an internal cooling air passageway, and the airfoil including an internal multi-bend heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, and a tip flag cooling system.

Abstract: A compressor system includes a gas compressor with dry gas seals about a driveshaft. The compressor system also includes a fugitive gas system having a gas conduit in fluid communication with a collection cavity in a collector coupled to the gas compressor to receive fugitive gas leaked through a pressurized gas leakage path. The fugitive gas system may be structured for flaring the gas, and includes a pressure control system with an accumulator tank, and a vent line for venting gas pressure and having a backpressure regulator therein. Fugitive combustible gas is conveyed through a flow restriction orifice downstream of the compressor.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel stem assembly for receiving and distributing fuel and an injector head receiving fuel from the fuel stem assembly. The injector head can include an injector body, swirler vanes, a pilot assembly, passages, and fuel galleries. The pilot assembly can include pilot struts and a pilot tube. The swirler vanes and pilot struts can include passages to transport the pilot fuel from the fuel stem assembly to the pilot tube.