43 results about "Engine tuning" patented technology

An information handling system cooling profile is adjusted as the hardware configuration of the information handling system changes with the addition or removal of processing components. A cooling profile engine adapts the cooling profile to adjust for a processing components thermal profile, such as by retrieving the thermal profile from the component and applying the thermal profile to a cooling profile table to retrieve a cooling profile associated with a configuration having the component. In one embodiment, cooling profile adjustments are managed through a network so that the adjusted cooling profile adapts to other information handling systems operating nearby, such as blade information handling systems of a blade server.

Tuning processes implemented by an auto-tune controller are provided for measuring and adjusting the combustion dynamics and the emission composition of a gas turbine (GT) engine via a tuning process. Initially, the tuning process includes monitoring parameters, such as combustion dynamics and emission composition. Upon determining that one or more of the monitored parameters exceed a critical value, these “out-of-tune” parameters are compared to a scanning order table. Upon comparison, the first out-of-tune parameter that is matched within the scanning order table is addressed. The first out-of-tune parameter is then plotted as overlaid slopes on respective graphs, where the graph represents a fuel-flow split. Typically, the slopes are plotted as a particular out-of-tune parameter against a particular fuel-flow split. The slopes for each graph are considered together by taking into account the combined impact on each out-of-tune parameter when a fuel-flow split is selected for adjustment.

Methods and systems are provided for improving engine knock control by accounting for a drop in charge cooling efficiency of a knock control fluid at higher temperatures. In response to the prediction of an elevated temperature of a knock control fluid at a time of release from a direct injector, a pulse width of the injection is adjusted. Any knock relief deficits are compensated for using alternate engine adjustments, such as boost or spark timing adjustments.

A trim balance for a gas turbine engine having a hollow rotatable rotor shaft includes an elongate support rod adapted for longitudinal accommodation within and mounting on an interior surface of the rotor shaft and one or more apertured balance weights supported on the support rod which extends through the weight apertures and a weight retainer for retaining the weights on the support rod.

The invention provides a calibration method and system for an engine intake model, and a computer readable storage medium. The calibration method comprises the steps that experimental design data areread, and the experimental data comprise a plurality of variable valve timing combinations and a plurality of to-be-calibrated working conditions; one of the variable valve timing combinations in theexperimental data is set as the target variable valve timing combination; the variable valve timing combinations of an engine are adjusted to be the target variable valve timing combinations step by step; parameters of the engine are adjusted step by step, so that the engine is adjusted to be in the to-be-calibrated working conditions, and operation parameters of the engine under the to-be-calibrated working conditions are measured; and after all the to-be-calibrated working conditions are calibrated, the other variable valve timing combinations in the experimental data are set as the target variable valve timing combinations in sequence. According to the calibration method and system for an engine intake model, the engine can be accurately adjusted to be in the to-be-calibrated working conditions, and the problems that the engine calibration efficiency is low, precision is insufficient, and safety performance is insufficient are solved.

The invention discloses a jet manned aerial vehicle, comprising a flight seat, two elastic buffer racks, four main propelling rockets, an armrest, an operating handle, two side flight systems, a rear turbojet engine, and a battery; the two elastic buffer racks are mounted symmetrically on the lower portion of the flight seat, the four main propelling rockets are mounted on the lower portion of the flight seat, the side flight systems are mounted symmetrically on two sides of the flight seat respectively, large parallel plates are mounted on the lateral side of the flight seat, one sides of upper and lower hinging plates are hinged to the large parallel plates respectively, the other sides of the upper and lower hinging plates are hinged to small parallel plates respectively, the small parallel plates and the large parallel plates are parallel to each other, cylinder block ends of hinging plate adjusting cylinders are hinged to the lower portions of the large parallel plates, and a piston rod end of an engine adjusting cylinder is hinged to the side turbojet engine. By providing the multi-angle adjustable flight system, flight is free and simple; the jet manned aerial vehicle is simple in structure and convenient to operate.

The invention discloses a jet manned aerial vehicle, comprising a flight seat, two elastic buffer racks, four main propelling rockets, an armrest, an operating handle, two side flight systems, a rear turbojet engine, and a battery; the two elastic buffer racks are mounted symmetrically on the lower portion of the flight seat, the four main propelling rockets are mounted on the lower portion of the flight seat, the side flight systems are mounted symmetrically on two sides of the flight seat respectively, large parallel plates are mounted on the lateral side of the flight seat, one sides of upper and lower hinging plates are hinged to the large parallel plates respectively, the other sides of the upper and lower hinging plates are hinged to small parallel plates respectively, the small parallel plates and the large parallel plates are parallel to each other, cylinder block ends of hinging plate adjusting cylinders are hinged to the lower portions of the large parallel plates, and a piston rod end of an engine adjusting cylinder is hinged to the side turbojet engine. By providing the multi-angle adjustable flight system, flight is free and simple; the jet manned aerial vehicle is simple in structure and convenient to operate.

The invention discloses a multifunctional timing sprocket cover, which comprises the timing sprocket cover, and is characterized in that: the timing chain and the camshaft exhaust side sprocket are located on the inner side of the timing sprocket cover There is a first chain guide groove at the point where the sprocket on the intake side of the camshaft is about to mesh and the point where the sprocket on the intake side of the camshaft is about to separate, and a second chain guide groove is set at the timing chain and the crankshaft sprocket; There are grooves at the top corresponding to the bolts of the intake camshaft and the bolts of the exhaust camshaft, and the semicircular rubber plugs are installed in the grooves; the timing sprocket cover consists of two parts, namely the metal part and the Corresponds to the transparent visible part at the hydraulic tensioner. This structure prevents the occurrence of tooth skipping in the timing chain system through the chain guide groove set on the timing chain cover, and simplifies the working procedure of the engine phase adjustment by setting a semi-circular rubber plug that can be easily disassembled. The viewing part is convenient for directly observing the working condition of the hydraulic tensioner.

The present invention generally relates to a simulated aircraft engine (12) accelerometer apparatus, system and method for generating an aircraft engine (12) simulator output. The accelerometer signal simulator (320) receives the aircraft engine (12) simulator output and generates the accelerometer signal simulator (320) output, and the accelerometer waveform generator (350) receives the accelerometer signal simulator (320) output, And at least one accelerometer signal simulator (320) output is synchronized with a reference timing signal from an aircraft engine (12) simulator output. The simulated accelerometer (300) also includes a filter section (372, 374, 376, 378) that receives the plurality of accelerometer waveform generator (350) outputs and filters out noise, thereby producing a plurality of filtered accelerometer waveform generator (350) output; a mixer (380) that receives and combines each of the multiple filtered accelerometer waveform generator (350) outputs to produce a single filtered accelerometer waveform generator (350 ) output; and a charge converter (382) that receives a single filtered accelerometer waveform generator (350) output and converts it to a current charge vibration simulation output.