A method of communication, within a processing system of a gas turbine engine, between a first electronic component and a second electronic component, comprising: generating by the first electronic component, a request, comprising a digital certificate, intern comprising a first host public key and a first client public key, signed with a first host private key, to initiate a trusted communication session with a second electronic component; encrypting at the first electronic component, at least a portion of the request with a first client private key; transmitting the request to the second electronic component; the first host private key and the first host public key defining a first asymmetric keypair and the first client private key and the first client public key defining a second asymmetric keypair.

Control systems and methods for securely authenticating and validating a control system. The control system may include a plurality of dependent control nodes and master control nodes. Each dependent control node is communicatively coupled to one or more peripheral devices. Each control node maintains a unit level distributed ledger, where each unit level distributed ledger includes information from corresponding peripheral devices. Each control node may transmit a portion of the unit level distributed ledger to a master control node. Each master control node may maintain a system level distributed ledger that includes information from the corresponding unit level distributed ledgers. Each master node may transmit a portion of the system level distributed ledger to a central node that maintains a separate secure distributed ledger. The master node may authenticate the control system based on the received portion of the system level distributed ledgers and the secure distributed ledgers.

A method for controlling an engine having a control module and smart nodes. The method includes maintaining a block chain ledger, which includes an information block from at least a preceding engine start, may be at the control module of the aircraft engine. The method also includes maintaining a hash of at least a digital certificate and data at one of the smart nodes; transmitting a message including the hash to the control module; receiving the message at the control module; determining a control hash based upon the information from at least a preceding engine start at the control module; module comparing the hash to the control hash at the control; and based upon the comparison, starting the engine and updating the block chain ledger as a function of the received message.

A cooling system with a thin walled cooling plate. The system includes an enclosure with a cover that defines an interior space and that has an open side. Temperature sensitive devices are contained in the interior space. A cooling plate closes the open side and includes an inner side with a surface that is substantially flat and that faces into the interior. The cooling plate defines a flow channel adjacent the inner side that is configured to channel a circulating fluid to remove heat from the interior space. The flow channel extends across substantially all of the opening. An outer side of the cooling plate may be anodized to block heat from entering the interior space through the cooling plate.

A networked electronic ordnance system is provided. The system includes a first plurality of pyrotechnic devices connected to a first network bus. The system further includes a first bus controller connected to the first network bus. The system further includes a second plurality of pyrotechnic devices connected to a second network bus. The system further includes a second bus controller connected to the second network bus. The system further includes a bus interface circuit connected to the first bus controller by a first electrical connection and connected to the second bus controller by a second electrical connection.

Disclosed is an active tip clearance control system (ATCCS) for a gas turbine engine, having an electronically controlled regulating valve directing cooling airflow to a turbine case, and an engine electronic control (EEC), controlling the electronically controlled regulating valve, wherein the EEC controls the electronically controlled regulating valve to regulate cooling airflow according to a selected target blade tip clearance schedule, and wherein the selected target blade tip clearance schedule is selected before or after an engine cycle, from of a plurality of target blade tip clearance schedules, each correlating to one of a plurality of thrust rating applications for the engine.

A transient cooling system includes a first phase change material (PCM) element and a second PCM element. The first PCM element includes a first PCM, a first surface, and a second surface, the first surface complementary to a surface to be cooled. The second PCM element includes a second PCM and a third surface in thermal contact with the second surface. The first PCM and the second PCM may have different thermal characteristics.

A method of monitoring a gas turbine engine start system includes monitoring a pressure in a starter air duct in communication with a starter air valve which is in communication with an air turbine starter (ATS); identifying an expected transient pressure response in the starter air duct; and identifying the starter air valve as degraded if the expected transient pressure response does not occur after an open command to the starter air valve.

A networked electronic ordnance system is provided. The system includes a first plurality of pyrotechnic devices connected to a first network bus. The system further includes a first bus controller connected to the first network bus. The system further includes a second plurality of pyrotechnic devices connected to a second network bus. The system further includes a second bus controller connected to the second network bus. The system further includes a bus interface circuit connected to the first bus controller by a first electrical connection and connected to the second bus controller by a second electrical connection.

A sensor system for identifying a transient sensor failure in an industrial system and for recovering from an erroneous estimation of an expected mass flow rate resulting from the transient sensor failure. The sensor system includes one or more sensors for measuring at least one fluid property of the industrial system. The sensor system includes an enhanced flow soft sensing (EFSS) computing device configured to determine an estimated mass flow rate. The EFSS computing device is also configured to generate expected measurements to be received from one or more sensors. If an error value is not within predetermined parameters, the transient sensor failure is detected. The EFSS computing device is further configured to identify a resurgence of the sensor from the transient sensor failure. An erroneous expected mass flow rate then converges toward a correct expected mass flow rate.