Bizarre Patents
Decorative Jeweled Wheel Cover
An improved wheel is provided wherein decorative items such as gem stones are embedded in either the wheel surface, a special mounting section attached to the wheel surface, or to a spoke strap that wraps around each spoke and positions embedded gem stones on the outside surface of the spoke.
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| Number | Title | Issue Date |
| 7366593 | Method and system for maneuvering movable object A movable object maneuver method wherein a destination point is set; wherein a thrust value is calculated in real time which minimizes or maximizes a performance index associated with one or more state variables and thrust required for a movable object to reach the ... | 04/29/2008 |
| 7207213 | Device for stabilizing the engine inlet flow in static tests of engines The invention relates to an apparatus for the stabilization of the engine inlet flow in engine static tests. It consists of an arrangement with an air-permeable element (4), which is arranged in an end position situated close to an engine housing (2) a... | 04/24/2007 |
| 7150560 | Device and method for determining total temperature for aircraft The invention relates to a device for determining total temperature for aircraft. This device is particularly useful in a probe, called a multifunction probe, for measuring several aerodynamic parameters such as, for example, the total pressure (Pt), the static pres... | 12/19/2006 |
| 7006905 | Method and device for allocating thrust Force balance and moment balance associated with thrust of air and water craft equipped with thrust generators are preset in view of non-linear characteristics and dynamic characteristics of thrust generators. A performance index for minimizing thrusts generated by ... | 02/28/2006 |
| 6941195 | Method and device for allocating thrust Force balance and moment balance associated with thrust of air and water craft equipped with thrust generators are preset in view of non-linear characteristics and dynamic characteristics of thrust generators. A performance index for minimizing thrusts generated by ... | 09/06/2005 |
| 6910370 | Apparatus and method for preventing inlet vortex A method of operating a gas turbine engine for testing, comprising: providing an aircraft on a tarmac, the aircraft having a gas turbine engine with an inlet; selecting a power setting for the engine that is capable of producing a vortex between the inlet and the ta... | 06/28/2005 |
| 6904340 | Flight control indicator for an aircraft, in particular a transport airplane, intended to supply the thrust generated by at least one engine of the aircraft Flight control indicator for an aircraft, in particular a transport airplane, intended to supply the thrust generated by at least one engine of the aircraft. The flight control indicator (1) comprises display means (4) which present, on a viewin... | 06/07/2005 |
| 6851303 | Method of determining thrust A method for determining the free-field thrust of a gas turbine engine using an enclosed gas turbine engine test facility without recourse to an outdoor gas turbine engine test facility. The method includes calculating the gas turbine engine intake momentum drag and... | 02/08/2005 |
| 6745622 | Apparatus and method for inspecting dovetail slot width for gas turbine engine disk An apparatus and method for inspecting a dovetail slot of a gas turbine engine disk, including: a first pin member fixed in a stationary position; a second pin member having the ability to move between a first position and a second position, wherein the second pin m... | 06/08/2004 |
| 6637932 | Engine thrust bearing condition monitoring method A method is provided for monitoring engine thrust bearing temperature deviations. Initially, key engine parameters are measured. A bearing temperature rise can be predicted based on the measured parameters. The predicted rise value is compared with the ac... | 10/28/2003 |
| 6568254 | Method for monitoring the creep behavior of rotating components of a compressor stage or turbine stage The present invention relates to a method for monitoring the creep behavior of rotating components of a compressor stage or turbine stage. In the method, at least one test element (2) is mounted in a region of the compressor stage or turbine stage in whic... | 05/27/2003 |
| 6497137 | Annular after reactor with sound attenuator for use in a jet engine test cell and test stand An annular after reactor is aligned axially with the direction of exhaust flow from the exhaust port of a jet engine under static test. Located near the front end of the reactor is a first set of gas injectors. A second set of gas injectors are located do... | 12/24/2002 |
| 6237395 | Annular after reactor for use with a jet engine test cell An annular after reactor is aligned axially with the direction of exhaust flow from the exhaust port of jet engine undergoing static test. Located near the front end of the annular after reactor is a first set of gas injectors which extend inward into the... | 05/29/2001 |
| 6162011 | Method and apparatus for stabilizing an intake air flow of a ground-based turbine engine When a turbine engine is operated near the ground, for example on a stationary static test stand, the ground effect as well as excessive lateral wind effects can lead to instabilities and unacceptable flow conditions of the air flow entering the air intak... | 12/19/2000 |
| 6032545 | Nozzle flow thrust vector measurement A nozzle flow thrust vector measurement system employs a thrust vector table, and a gas supply. The thrust vector table employs a thrust measurement table; a reference table; and at least three load cell assemblies coupled to the thrust measurement table ... | 03/07/2000 |
| 5893040 | Method and apparatus for automatically providing jet engine thrust ratings to avionic systems An avionic system (102) in which engine thrust rating data is transmitted from electronic engine controllers (108a and 108b) to flight management computer/thrust management computers (120a and 120b) via digital data buses (110a, 110c, and 114) is disclose... | 04/06/1999 |
| 5831155 | Apparatus and method for simulating rocket-to-ramjet transition in a propulsion system A test facility for realistically simulating selected operating conditions for a multi-mode aircraft propulsion system employs bypass ducting to rapidly introduce heated compressed air to a ramjet engine immediately following rocket booster operation. Hea... | 11/03/1998 |
| 5591904 | Apparatus for diminishing intake vortexes in jet engines For the purpose of diminishing intake vortexes at jet engines with turbo-compressors of aircrafts, in particular during test runs, an apparatus is provided, which consists of a grating disposed near the ground below and directly in front of the engine inl... | 01/07/1997 |
| 5589632 | Method and device for estimating the thrust of a ramjet The combustion chamber of the ramjet is mounted on a support which allows partial freedom of longitudinal movement. A nozzle is arranged at the intake of the combustion chamber, with a flexible, fluid-filled bladder being disposed between the nozzle and t... | 12/31/1996 |
| 5524494 | Aircraft propeller thrust measurement apparatus In present day propeller driven aircraft, the engine is mounted on slightly resilient engine mounts which in turn are secured to the aircraft fuselage. Under propeller rotation, the developed thrust causes the engine housing to move slightly forward relat... | 06/11/1996 |
| 5517852 | Diagnostic performance testing for gas turbine engines An improved gas turbine engine diagnostic system is disclosed which is particularly adapted for direct measurement of compressor performance, including efficiency and mass flow, for aircraft engines, without having to remove the engine form the aircraft. ... | 05/21/1996 |
| 5479350 | Exhaust gas temperature indicator for a gas turbine engine An exhaust gas temperature indicator for a gas turbine engine is disclosed in which data representing discrete overtemperature events occurring at different times is stored in a nonvolatile memory for later retrieval and display on an event-by-event basis... | 12/26/1995 |
| 5431045 | Device and method for measuring on earth the thrust of thrusters for use in space The equipment for measuring on earth the thrust of thrusters for use in space comprises a balance (1) and a measuring means (11) which is associated with the balance in order to measure the thrust exerted by the thruster (P). The balance (1) is provided w... | 07/11/1995 |
| 5396793 | Altitude gas turbine engine test cell The test cell has a pressure recovery pipe (26) receiving air from the tested engine (14). Excess air is inherently induced into the pipe. A source flow path for this excess air is provided from within the pipe (36) back to the entrance the pipe passing t... | 03/14/1995 |
| 5383355 | Gas turbine engine inspection system A system for the examination or inspection of a gas turbine engine in which a computer 3 controls a series of probes by way of devices for controlling movements in different directions. Thus, there is a centralized control of the measurements for allowing... | 01/24/1995 |
| 5235848 | Thruster test fixture The device to be tested is supported from a beam by two parallel links so e thrust direction remains perpendicular to the direction of gravity. Each link is connected to the beam by a tension transducer also oriented perpendicular to the direction of grav... | 08/17/1993 |
| 5178002 | Spectroscopy-based thrust sensor for high-speed gaseous flows A system and method for non-intrusively obtaining the thrust value of combustion by-products of a jet engine is disclosed herein. The system includes laser elements for inducing absorption for use in determining the axial velocity and density of the jet f... | 01/12/1993 |
| 5170662 | Balance for measuring the thrust of a turbojet engine A balance for measuring the thrust of a turbojet engine comprises a movable frame suspended by flexible suspension strips from an interface structure fixed to the ceiling of a building housing the balance, an adaptor by which the turbojet engine is mounte... | 12/15/1992 |
| 5152169 | Gas turbine engine thrust measurement The thrust produced by a gas turbine engine can be calculated from the rate at which fuel is consumed by the engine. At a constant air temperature and pressure the thrust produced by the engine is proportional to the rate of fuel consumption.... | 10/06/1992 |
| 4833911 | System for measuring aircraft engine thrust The present invention comprises a system for measuring the thrust delivered by aircraft engines which rely on induced flow for their propulsive effect. In the preferred embodiment, for use in conjunction with turboprop engines, the system includes mechani... | 05/30/1989 |
| 4788855 | Test apparatus for measuring jet engine thrust Apparatus for simultaneously measuring the torque generated by a bladed turbofan engine as well as the forward force generated by gases exhausted from the turbofan engine in order to calculate total thrust. The apparatus includes a cradle for suspending t... | 12/06/1988 |
| 4787053 | Comprehensive engine monitor and recorder A comprehensive turbine engine monitoring and recording system includes an electronics unit which may be engine mounted, and which contains at least a nonvolatile memory and a data-processor, for use with a remote unit suitable for either cockpit mounting... | 11/22/1988 |
| 4570490 | Differential pressure ratio measurement system A pressure ratio measuring system is disclosed. The system includes two quartz capacitive pressure transducers (16, 22). Each capsule contains a pressure sensitive capacitor (Csa, Csf) which is fed by an alternating excitation signal. Capacitance (Csa) is... | 02/18/1986 |
| 4546353 | Asymmetric thrust warning system for dual engine aircraft An asymmetric thrust warning system for an aircraft having two gas turbine engines. The compressor discharge pressures of the two engines are compared to determine the engine providing the lower thrust and to provide a signal indicative of the actual diff... | 10/08/1985 |
| 4537066 | Aeroengine test cells Measurements of net thrust of an aeroengine on a thrust balance in a test cell must be corrected to gross thrust and it is also advantageous to detect changes in the airflows into and through the test cell of a magnitude sufficient to alter significantly ... | 08/27/1985 |
| 4535412 | Drivetrain torque determination using torque converter characteristics A system for determining the instantaneous torque produced by an engine or motor that drives on automotive vehicle powertrain through a hydrodynamic torque converter. A digital circuit operates to generate a binary number, which is the count of high frequ... | 08/13/1985 |
| 4534216 | Method and apparatus for determining the accuracy of wind tunnel test data The accuracy of performance data obtained from instrumentation associated with a wind tunnel test facility is determined by a comparison of empirically and analytically determined performance data associated with a combustorless gas turbine engine referen... | 08/13/1985 |
| 4517648 | Torque variation detecting method and apparatus for internal combustion engine A torque variation in an internal combustion engine due to the combustion variations is detected at each predetermined period. An average torque variation to be compared with the detected torque variation is predetermined experimentally based on the engin... | 05/14/1985 |
| 4505153 | Recoil transducer fixture A recoil transducer fixture for determining force responses at high frequies. An impact transducer is mounted in a rigid assembly and is preloaded for operating under compressive loads. The fixture includes a pair of spaced plates having the transducer m... | 03/19/1985 |
| 4434664 | Pressure ratio measurement system A pressure ratio measuring system is disclosed. The system includes two quartz capacitive pressure transducers (16, 22). Each capsule contains a pressure sensitive capacitor (Csa, Csf) which is fed by an alternating excitation signal. Capacitance (Csa) is... | 03/06/1984 |