50 results about "Redline" patented technology

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

The invention discloses a liquid oxygen methane rocket engine fault prediction method and system based on an ARMA model, and the method comprises the steps: constructing a modularized simulation model of a liquid oxygen methane rocket engine, injecting fault factors to simulate typical faults (such as methane pump cavitation, turbine blade ablation and the like), and obtaining normal and fault data containing Gaussian noise; carrying out time sequence modeling on the six key parameters by adopting an ARMA (Autoregressive Moving Average Model), and optimizing model parameters through ACF / PACF order determination and AIC criteria; establishing a self-adaptive residual threshold formula (threshold = residual mean + / -2 times of standard deviation), and realizing early warning of the fault by combining a judgment criterion that the threshold is continuously exceeded for three times and three parameters cooperatively give an alarm; experiments show that the alarm time is 0.1-0.13 seconds earlier than that of a traditional red line threshold method, the false alarm rate is reduced from 18.7% to 0.3%, and the spaceflight-level real-time performance and reliability requirements are met; the method does not need a large number of fault samples, is high in anti-interference capability, and is suitable for online health monitoring of reusable rocket engines.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000). In some instances, a gas turbine engine also comprises a gearbox efficiency rating and / or an overall efficiency rating.

A turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a HPC defining a HPC exit area (AHPCExit) in square inches, the turbine section having a LPT; a fan; a gearbox; and a DECP 0.10-0.50, where DECP equals 10*D / GR / NLPT2 / NHPC, D is the fan blade tip diameter, GR is the gear ratio of the gearbox, NLPT is the stage count of the LPT, and NHPC is the stage count of the HPC. The gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

In an electric vehicle where the torque output of the electric motor is adapted to change in response to input from the driver to simulate the torque characteristics of a virtual engine, the rotational state of the virtual engine is clearly displayed to the driver while minimizing wasted screen resources on the display screen. [Solution] According to one embodiment, the control device for an electric vehicle displays a pointer 310 representing the virtual rotational speed of a virtual engine on a display screen. In the rotational speed range below the redline rotational speed of the virtual engine, the control device continuously moves the pointer 310 within the first display area 311 of the display screen according to the magnitude of the virtual engine rotational speed. In the rotational speed range above the redline rotational speed, the control device moves the pointer 310 to the second display area 312 outside the first display area 311, and restricts the movement of the pointer 310 in the second display area 312 regardless of the magnitude of the virtual rotational speed.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A turbomachine engine including an engine core including a high-pressure compressor, which has an exit stage having an exit stage diameter (DCORE), a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, a power turbine in flow communication with the high-pressure turbine, and a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft / sec)1 / 2 and three hundred (ft / sec)1 / 2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft / sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. The low-pressure shaft has a length (LMSR) defined by an engine core length (LCORE) given by:LCORE=[m(20+m)*n(10+n)](1100)*DCORE+CIS.

The invention relates to an electric vehicle. In an electric vehicle suitable for changing the torque output by an electric motor so as to simulate the torque characteristics of a virtual engine in response to an operation input from a driver, the rotation state of the virtual engine is easily understood by the driver while suppressing waste of screen resources of a display screen. According to one embodiment, a control device for an electric vehicle displays, on a display screen, a pointer (310) indicating a virtual rotational speed of a virtual engine. In a rotation speed region equal to or less than the red line rotation speed of the virtual engine, the control device continuously moves the pointer (310) in accordance with the magnitude of the virtual engine rotation speed in a first display region (311) of the display screen. In a rotational speed region higher than the red-line rotational speed, the control device moves the pointer (310) to a second display region (312) other than the first display region (311), and restricts the movement of the pointer (310) in the second display region (312) regardless of the magnitude of the virtual rotational speed.

A gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; a fan; a gearbox; and an engine correlation parameter of 0.17-0.83, where the engine correlation parameter equals D / N / GR, D is the blade tip diameter measured in feet, N is the stage count of the low-pressure turbine, and GR is the gear ratio of the gearbox. The gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; and a component within the turbomachine, the component including a nickel-based superalloy. The gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A turbomachine engine including an engine core including a high-pressure compressor, which has an exit stage having an exit stage diameter (DCORE), a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, a power turbine in flow communication with the high-pressure turbine, and a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft / sec)1 / 2 and three hundred (ft / sec)1 / 2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft / sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. The low-pressure shaft has a length (LMSR) defined by an engine core length (LCORE) given by:LCORE=[m  (20+m)*n  (10+n)](1100)*DCORE+CIS.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A gas turbine includes a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order. The compressor section includes a high pressure compressor defining a high pressure compressor exit area (AHPCExit). The turbine section includes a low pressure turbine having at least a first stage of turbine rotor blades and a first stage of turbine stator vanes. The gas turbine engine defines a redline exhaust gas temperature (EGT), a total sea level static thrust output (FnTotal), an airfoil density (ρ) of one or both of the first stage of turbine rotor blades and the first stage of the turbine stator vanes, and a corrected specific thrust.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000). The gas turbine engine further includes a blade effective acoustic length (BEAL), an acoustic spacing, and an acoustic spacing ratio (ASR). The ASR can be in a range from 1.5 to 16.0.

The invention provides an adjusting device, method, system and equipment for adjusting states of three red lines of an engine, and relates to the field of airworthiness verification tests of the engine, the adjusting device comprises a swirler, the swirler is arranged in an air inlet channel of the engine, and the swirler is arranged perpendicular to the axis of the engine. The swirler comprises a swirl guide vane which can rotate in the radial direction of the engine, so that the pre-swirl angle of the swirler is adjustable. According to the invention, the thrust of the engine is effectively reduced by controlling the rotation of the rotational flow guide vane, adjusting the pre-rotation angle of the swirler and reducing the flow of the outer culvert airflow of the engine, so that the engine is prevented from generating excessive thrust, and the thrust of the engine does not exceed the red line state too much when the rotating speed of the rotor reaches the red line state; the strength and the service life of key components such as an engine fan, a gas compressor and a turbine are ensured.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A turbomachine engine including a high-pressure compressor, a high-pressure turbine, a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, and a power turbine in flow communication with the high-pressure turbine. At least one of the high-pressure compressor, the high-pressure turbine, and the power turbine comprises a ceramic matrix composite (CMC) material. The turbomachine engine includes a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft / sec)1 / 2 and three hundred (ft / sec)1 / 2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft / sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft.

A gas turbine engine includes a turbomachine having an engine core including a high-pressure compressor, a combustion section, a high-pressure turbine, and a high-pressure shaft coupled to the high-pressure compressor and the high-pressure turbine. The engine core has a length (LCORE), and the high-pressure compressor has an exit stage diameter (DCORE). The high-pressure compressor defines a high-pressure compressor exit area (AHPCExit) in square inches. The gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000). The high-pressure shaft is characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and a ratio of LCORE / DCORE is from 2.1 to 4.3.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A turbomachine engine includes an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber. The engine core has a length (LCORE), and the high-pressure compressor has an exit stage diameter (DCORE). A power turbine is in flow communication with the high-pressure turbine. A low-pressure shaft is coupled to the power turbine and characterized by a midshaft rating from one hundred fifty (ft / sec)1 / 2 to three hundred thirty (ft / sec)1 / 2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second. The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. A high-pressure shaft is coupled to the high-pressure compressor and the high-pressure turbine and is characterized by a high-speed shaft rating from 1.5 to 6.2, and a ratio of LCORE / DCORE is from 2.1 to 4.3.

A gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section, the compressor section having a high-pressure compressor defining a high-pressure compressor exit area (AHPCExit) in square inches. The high-pressure compressor includes a high-pressure compressor flowpath and a plurality of stages. A bleed system includes a plurality of bleed flowpaths that direct compressed air from the high-pressure compressor flowpath. At least two of the bleed flowpaths are at successive stages of the plurality of stages. The gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000). The gas turbine engine further includes a blade effective acoustic length (BEAL), an acoustic spacing, and an acoustic spacing ratio (ASR). The ASR can be in a range from 1.5 to 16.0.

A gas turbine engine includes a turbomachine having an engine core including a high-pressure compressor, a combustion section, a high-pressure turbine, and a high-pressure shaft coupled to the high-pressure compressor and the high-pressure turbine. The engine core has a length (LCORE), and the high-pressure compressor has an exit stage diameter (DCORE). The high-pressure compressor defines a high-pressure compressor exit area (AHPCExit) in square inches. The gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000). The high-pressure shaft is characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and a ratio of LCORE / DCORE is from 2.1 to 4.3.

The electric vehicle is adapted to change the torque output by an electric motor to simulate the rotational speed-torque characteristic of a virtual rotating machine in response to driver operation. The electric vehicle comprises a display device and a control device. The control device displays on a display screen of the display device an indicator representing a virtual rotational speed of the virtual rotating machine. In a rotational speed range below the redline rotational speed of the virtual rotating machine, the control device continuously or discretely moves the indicator within a first display area of the display screen according to the magnitude of the virtual rotational speed. In a rotational speed range higher than the redline rotational speed, the control device moves the indicator to a second display area outside the first display area, and limits the movement of the indicator within the second display area.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000). In some instances, a gas turbine engine also comprises a gearbox efficiency rating and / or an overall efficiency rating.

A gas turbine engine includes a turbomachine having an engine core including a high-pressure compressor, a combustion section, a high-pressure turbine, and a high-pressure shaft coupled to the high-pressure compressor and the high-pressure turbine. The engine core has a length (LCORE), and the high-pressure compressor has an exit stage diameter (DCORE). The high-pressure compressor defines a high-pressure compressor exit area (AHPCExit) in square inches. The gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000). The high-pressure shaft is characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and a ratio of LCORE / DCORE is from 2.1 to 4.3.