A clamp for securing a component to an isogrid case of a gas turbine engine includes a top having an attachment feature for coupling the clamp to the component. The clamp further includes a bottom. The clamp further includes two sides extending from the top towards the bottom, each of the two sides being thicker at the bottom than at the top, and the two sides defining a shaped slot closer to the bottom than the top for receiving a rib of the isogrid case.

In one embodiment, a computing device includes one or more processors configured to execute instructions that cause the one or more processors to acquire pressure data measured by at least one pressure sensor disposed proximate to a filter house in an intake of a gas turbine engine system, derive an airflow or an air mass flow through a duct of the intake using a thermodynamic model of the gas turbine engine system based at least on the pressure data, derive an intake pressure drop in the duct using at least the pressure data, derive a loss parameter of the filter house by combining the air mass or air mass flow, and the intake pressure drop, derive a pressure loss model based on the loss parameter over a period of time, and determine a condition of the filter house based on the pressure loss model.

Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including a backup intersegment seal disposed in the slot on a high-pressure side of the slot and a shim seal disposed in the slot over the backup intersegment seal and covering the backup intersegment seal on a low-pressure side of the slot. The shim seal including one or more shim seal segments and having a gap formed between each of the one or more shim seal segments.

The present disclosure is directed to a system and method for repairing an abradable material coated on a casing of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the gas turbine engine. Further, the articulating guide has a proximal end and a distal end. The system also includes a repair tool configured at a distal end of the articulating guide. The repair tool includes a body having a proximal end and a shaped distal end, with the shaped distal end extending away from the body. Thus, the shaped distal body is configured to trench out an area of the abradable material comprising a defect. The system also includes a filler material for filling the trenched out area.

A system and method for detecting the rotation breakaway of a spacer from a compressor rotor disk are disclosed herein. The method includes detecting a disk sensed feature and a spacer sensed feature on the compressor rotor disk and the spacer respectively. The method also includes comparing the timing between the two to a predetermined threshold to determine whether the relative position of the spacer to the compressor rotor disk exceeds a predetermined amount. The predetermined amount may be selected to determine whether an imbalance, rubbing, or binding can occur in the gas turbine engine or to determine whether anti-rotation features have been broken.

The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform can be increased, hence reducing the quantity of the air needed.

A combustor for a gas turbine engine comprises an inner annular liner wall and an outer annular liner wall cooperating to form a combustion chamber of the combustor. A first dome wall has a circumferential array of first fuel injection bores. A second dome has a circumferential array of second fuel injection bores. An intermediate wall extends between the first dome wall and the second dome wall. A first combustion stage is defined by the inner liner wall forward end, the first dome wall and the intermediate wall. A second combustion stage is defined at least by the outer liner wall forward end, the second dome wall and the intermediate wall, the first combustion stage communicating with the first fuel injection bores, the second combustion stage communicating with the second fuel injection bores.

A turbo machine, a computer-implemented method, and a computer system for operating a compressor assembly are provided. The method includes comparing a first data set and a second data set to determine a first correlation factor, comparing the first correlation factor to a first threshold that at least partially determines whether a stall precursor exists, removing mean values from the first data set and the second data set, comparing the first data set and the second data set each removed of mean values to determine a second correlation factor, and comparing the second correlation factor to the first threshold, and classifying the stall precursor as either a spike stall precursor, a modal stall precursor, or a combination stall precursor.

A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.

A turbo machine, a computer-implemented method, and a computer system for operating a compressor assembly are provided. The method includes comparing a first data set and a second data set to determine a first correlation factor, comparing the first correlation factor to a first threshold that at least partially determines whether a stall precursor exists, removing mean values from the first data set and the second data set, comparing the first data set and the second data set each removed of mean values to determine a second correlation factor, and comparing the second correlation factor to the first threshold, and classifying the stall precursor as either a spike stall precursor, a modal stall precursor, or a combination stall precursor.