1336 results about "Fuel pump" patented technology

The invention relates to the technical field of digital pump operation control, in particular to a digital pump operation method and system, and provides the following scheme that winding temperature gradient distribution, axial strain and cooling liquid dielectric property parameters are collected and input into a preset finite element thermal model, boundary conditions are corrected by adopting an adjoint matrix method, and the temperature gradient distribution, the axial strain and the cooling liquid dielectric property parameters are obtained. And reconstructing a three-dimensional transient heat flux density field to realize precise positioning of a local overheating area. Contribution of a heat source item to a temperature field is calculated based on sensitivity analysis, a heat flow density field is optimized in combination with the Fourier law, and calculation precision is improved. The device is suitable for the fields of urban water supply, petrochemical engineering, aviation fuel pumps and the like, the heat management precision of equipment can be improved, the service life is prolonged, and the operation efficiency is improved.

The invention relates to the technical field of test bed operation monitoring, in particular to a fuel pump test bed operation monitoring method and system. The method comprises the following steps: acquiring monitoring time sequence data of operation of a fuel pump test bed, performing feature extraction, constructing a coupling prediction model of a space-time diagram attention network-unscented Kalman filter, and predicting a process noise covariance matrix and a measurement noise covariance matrix according to the coupling prediction model, and performing state estimation by using an unscented Kalman filter to obtain vector posterior probability distribution, constructing a fault evolution trajectory manifold, calculating a mahalanobis distance between the vector posterior probability distribution and the fault evolution trajectory manifold, and taking the mahalanobis distance as a monitoring index. According to the scheme of the invention, the deep features which can better reflect the inherent nonlinear and complex dynamic characteristics of the system can be extracted from the multi-source data, the estimation accuracy of the filter on the potential health state of the system is improved, and the defects that model parameters are fixed and gradual change faults are difficult to capture in a traditional method are overcome.

A fuel pump module for a vehicle includes: a pump positioned in a reservoir cup in a tank and configured to suction and discharge fuel from the reservoir cup; a mount plate mounted in an opening of the tank; a return valve on the mount plate and configured to pass return fuel, which is returned from an engine, into the tank; a shaft bracket connecting the mount plate and the pump in the tank and configured to fix the pump to the mount plate; a guide wall disposed on the shaft bracket to guide return fuel flowing in the tank through the return valve; and a channel disposed at the shaft bracket so that return fuel flows down and configured to discharge the return fuel into the reservoir cup.

A method of operating an aircraft gas turbine engine including: a core including a turbine, a compressor, a combustor, and a core shaft connecting the turbine to the compressor; a fan upstream of the core; a fan shaft; at least one bearing supporting the fan shaft; at least one auxiliary system using some of the fuel; an oil loop system to supply oil to the bearing; and a heat exchange system including: a primary fuel-oil heat exchanger through which oil in the oil loop system and substantially all the fuel flow to transfer heat between the oil and the fuel; and a secondary fuel-oil heat exchanger through which oil in the oil loop system and a portion of the fuel flow, to transfer heat between the oil and the fuel; and a fuel pump; wherein, under cruise conditions, fuel temperature on leaving the second heat exchanger is 120° C. to 200° C.

An aircraft fuel system includes a fuel tank, a fuel pump configured to receive a fuel flow from the fuel tank via a fuel supply line. The fuel system further includes a tap fluidly coupled to an outlet of the fuel pump, at least one generator or permanent magnet machine fluidly connected to the fuel pump via the tap, and the tap is configured to deliver fuel to the at least one generator or permanent magnet machine. The fuel system further includes a gearbox mechanically connected to the at least one generator or permanent magnet machine.

To provide a fuel pump and fuel injection system that can pressurize a plurality of kinds of fuels in a simple structure.SOLUTION: A fuel pump 10 comprises a first piston 16, a first pressure rising chamber 11, a second piston 21, and a second pressure rising chamber 12a. The first piston 16 is reciprocated by being pushed by a cam 13. The first pressure rising chamber 11 houses a first fuel to be pressurized by the first piston 16, and comprises a first discharge hole 18 for discharging the first fuel. The second piston 21 is reciprocated by being pushed by the first fuel pressurized by the first piston 16. The second pressure rising chamber 12a houses a second fuel to be pressurized by the second piston, and comprises a second discharge hole 23 for discharging the second fuel.SELECTED DRAWING: Figure 1

The embodiment of the invention discloses a fault diagnosis device of a permanent magnet synchronous motor driving system for an electric fuel pump, which is arranged in the permanent magnet synchronous motor driving system and comprises a three-phase voltage and current monitoring module connected to the output end of a permanent magnet synchronous motor, the motor rotating speed acquisition module is arranged on a rotor of the permanent magnet synchronous motor; the permanent magnet synchronous motor turn-to-turn short circuit fault diagnosis module, the permanent magnet synchronous motor uniform demagnetization fault diagnosis module, the permanent magnet synchronous motor local demagnetization fault diagnosis module, the inverter single-tube fault diagnosis module and the rotary transformer fault diagnosis module are arranged in the motor controller. The permanent magnet synchronous motor driving system provided with the fault diagnosis device provided by the embodiment of the invention has diagnosis capability, can realize online calculation and is rapid in diagnosis, so that the fault can be found in time, and technical support is provided for further eliminating the fault hidden danger in the subsequent process.

The invention relates to an aero-engine main fuel pump regulator parameter swing global closed-loop control method. The problem that at present, parameter swing faults can only be detected through engine test run is solved. According to statistical analysis of test data of an aero-engine, the rotating speed n2, P2 air pressure, S1 duty ratio and S8 duty ratio parameters of a main fuel pump regulator are controlled through a PID controller on a main fuel pump regulator performance tester under the conditions of simulating different accelerator handle angles and different temperature instruction pressures, so that actual values of follow-up piston displacement, alpha1 and alpha2 parameters are close to expected values, and the actual values of the follow-up piston displacement, alpha1 and alpha2 parameters are close to expected values. And global closed-loop control of the rotating speed and the guide vane angle is realized. The global closed-loop controller comprises an analog sampling module, an analog voltage control module, a signal control module, an upper computer module, a server module, a power supply module, an MCU module and a sensor module. According to the invention, the detection of the aero-engine parameter swing fault on the main fuel pump regulator performance tester is realized, and the occurrence of the parameter swing fault is effectively suppressed.

The invention relates to the technical field of fuel pump control, and particularly discloses an intelligent control method and system based on an intelligent integrated fuel pump, and the method comprises the steps that the intelligent integrated fuel pump is started to output fuel, and a fuel pressure sensor collects a pipeline fuel pressure signal in real time, converts the pipeline fuel pressure signal into a voltage signal and transmits the voltage signal to a CPU; the CPU presets fuel pressure values required by the engine under different working conditions, converts the received voltage signal into a fuel pressure value, compares the fuel pressure value with a set value, and generates an execution signal according to a comparison result; the processor adjusts fuel pump power supply voltage according to the execution signal and changes the rotating speed of a fuel pump motor; the PCBA temperature control module comprises a temperature sensor installed in the intelligent integrated fuel pump, and the temperature sensor senses the temperature rise condition of the PCBA in real time. Through cooperative work of the CPU, the processor and the fuel pressure sensor, accurate adjustment of the fuel pressure is achieved, and the working stability of the engine and the fuel utilization rate are improved.

The invention belongs to the technical field of offshore refueling, and discloses helicopter offshore platform refueling equipment, and a bearing bracket of an oil storage unit of the helicopter offshore platform refueling equipment comprises a fixed bracket, a sliding bracket for mounting a tank box assembly and a release mechanism; a first sliding face is arranged on the fixed support, the sliding support is arranged above the fixed support and provided with a second sliding face matched with the first sliding face, the releasing mechanism has the state of locking the sliding support and the state of releasing the sliding support, and the sliding support can slide down along the fixed support under the action of self gravity when being released. The pump skid unit of the refueling equipment is used for pumping fuel oil in the tank box assembly into the refueling skid unit, and finally refueling is conducted on the helicopter through the refueling gun. An electrostatic grounding protection reel is arranged in the refueling pry unit, the refueling gun is communicated with an outlet of the oil pump assembly, the electrostatic grounding protection reel comprises a grounding clamp, and a grounding needle is arranged on the inner wall of the clamping end of the grounding clamp in a protruding mode. The refueling equipment can deal with safety accidents in emergency, reduce the risk of electric shock and eliminate potential safety hazards.

The invention relates to an automatic assembling machine for fuel pump accessories, which comprises a machine table, an indexing turntable arranged on the machine table, and a first driving piece for driving the indexing turntable to rotate, a wire assembly station, a hot riveting station, an electric brush cover feeding assembly station, a corrugated pipe clamp assembly station, a clamp clamping station, a filter screen assembly station, a feeding station and a discharging station are arranged on the machine table in the circumferential direction of the indexing rotary disc, and the wire assembly station comprises a wire press-fitting block and a second driving piece for driving the wire press-fitting block to ascend and descend. The hot riveting station comprises a hot riveting piece and a third driving piece for driving the hot riveting piece to ascend and descend. The electric brush cover feeding and assembling station comprises an electric brush cover feeding mechanism and an electric brush cover assembling mechanism. By the adoption of the technical scheme, the automatic assembling machine for the fuel pump accessories can achieve automatic assembling, manual accessory installation is not needed, the assembling efficiency is greatly improved, and the automatic assembling machine is safer and high in percent of pass.

The invention belongs to the field of target drone fuel oil systems, and particularly relates to a self-adaptive supersonic speed target drone fuel oil system and a control method thereof. The system comprises a machine body oil tank, a first electromagnetic valve, an overflow valve, a pressurization oil tank, a fuel pump, an engine pump, a monitoring module and a control module. The body fuel tank comprises a main fuel tank and an auxiliary fuel tank which are arranged in a fuel tank in the middle of the target drone body and located in front of and behind the theoretical mass center of the target drone respectively. The pressurization oil tank is additionally arranged in the fuel oil cabin, fuel oil in the engine body oil tank enters the pressurization oil tank for pressure maintaining after being pressurized by the fuel oil pump, and then oil is supplied to the engine from the pressurization oil tank, so that stable oil supply to the engine is achieved by establishing a local pressure environment instead of a large pressure environment of the whole fuel oil cabin, and therefore when a fuel oil system works, the fuel oil can be stably supplied to the engine. The oil supply flow and pressure are controlled in a closed-loop mode in real time through the control system according to the engine state.

A fuel system for a hydrogen fueled aircraft propulsion system comprises first and second hydrogen fuel tanks configured to store liquid hydrogen, first fuel line and second fuel lines configured to supply hydrogen from the first hydrogen fuel tank to a combustor of a first gas turbine engine and from the second hydrogen fuel tank to a combustor of a second gas turbine engine respectively. First and second fuel pumps are provided, each being configured to pump fuel in a respective first and second fuel line. First and second fuel heaters are provided, each being configured to heat fuel in a respective first and second fuel line. A fuel cross-feed fuel line is provided, which is configured to transfer fuel between the first and second fuel lines. The fuel cross-feed line is provided downstream in fuel flow of the first and second fuel heaters.

The invention belongs to the technical field of aero-engine control, and discloses an electric fuel pump active-disturbance-rejection control method based on a radial basis function neural network. According to the method, an intelligent control system is constructed through a radial basis function neural network, an active-disturbance-rejection controller with a nonlinear state error feedback control law as a core is designed, a control strategy is adjusted in real time according to the current state of the system, the complexity of controller parameter setting is reduced, and the stability and response speed of the system are improved. Through verification, the electric fuel pump control system obtained through the design can achieve the stable and rapid control effect under all working conditions, and is high in practicability, good in system robustness and high in anti-interference capacity.

The invention particularly relates to a parallel combination engine starting and fuel oil supply system cross-linking structure and a control method, and the parallel combination engine starting and fuel oil supply system cross-linking structure comprises an air turbine, an aircraft accessory cartridge receiver, an engine transmission system and a stamping fuel oil pump; an air turbine shaft is connected with an aircraft accessory casing, a starting clutch is arranged between the air turbine shaft and the aircraft accessory casing, the aircraft accessory casing is connected with an engine transmission system, and the engine transmission system is connected with a turbine engine; an air turbine shaft is connected with a ramjet fuel pump, an oil supply clutch is arranged between the air turbine shaft and the ramjet fuel pump, and the ramjet fuel pump is used for The air turbine is connected with an airplane auxiliary power system through an air entraining pipeline; an auxiliary air entraining valve is arranged on the air entraining pipeline; the air turbine is connected with the turbine engine fan rear flow channel through an air entraining pipeline, and a fan air entraining valve is arranged on the air entraining pipeline. The air turbine is connected with the stamping air inlet channel through an air entraining pipeline, and a stamping air entraining valve is arranged on the air entraining pipeline.

The invention discloses an impact resistance test device for a marine diesel engine. The impact resistance test device comprises an impact resistance test bed, the upper end of the shock resistance test bench is connected with the test base; a plurality of vibration isolators are mounted on the test base, and anti-impact machine legs, fixedly connected with the bottom of a diesel engine, at the upper ends of the vibration isolators are connected with an impact hammer and are arranged on the outer side of the impact test bed for impacting the impact test bed; the data acquisition instrument is in circuit connection with the upper computer; and the data acquisition instrument is in circuit connection with an ECU (Electronic Control Unit) of the diesel engine, the external fuel pump and the pneumatic motor. The impact force borne by the diesel engine in the operation state when a ship is subjected to explosion impact is simulated on the land, and the working performance of the diesel engine can be detected when the diesel engine is subjected to impact resistance. And accessory equipment connected with the diesel engine is not arranged on the test bed and is flexibly connected with the diesel engine, so that the reliability is high, the device can be repeatedly used, and the test cost is reduced.

The invention belongs to the technical field of scramjet engine control, and particularly relates to a semi-physical simulation test platform of a scramjet engine control system, which comprises a fuel supply and control system, an engine simulator system, a flight control simulation system, a sensor simulation system, an upper computer management system and the like. The test platform can provide test equipment support for development (including control law research, control parameter optimization, performance prediction, fault diagnosis and the like) of a scramjet engine control system, and comprehensively examine system matching performance and control performance of key components such as a controller, a fuel pump, a fuel valve and the like. And stable and reliable operation of the scramjet engine control system is guaranteed.

The utility model relates to an oil supply system, a power driving system and an aircraft, the oil supply system is connected with an engine and an oil tank, the oil supply system comprises an oil supply pipeline, a fuel pump and a one-way valve, and the fuel pump and the one-way valve are arranged on the oil supply pipeline between the engine and the oil tank; the multiple fuel pumps and the multiple one-way valves are arranged, the multiple fuel pumps are connected in series, the multiple one-way valves are connected in series, the fuel pumps and the one-way valves are arranged in parallel, and the multiple fuel pumps and the one-way valves are connected through oil supply pipelines. A plurality of fuel pumps and a plurality of one-way valves are arranged in series, the fuel pumps and the one-way valves are arranged in parallel, the fuel pumps and the one-way valves are communicated through oil supply pipelines, and various oil supply channels are formed between the fuel pumps and the one-way valves, so that the situation that a fuel system cannot work normally due to faults of a single fuel pump or one-way valve can be avoided; and the safety and the reliability of the oil supply system are improved.

The fireproof accessory transmission casing comprises a first casing body and a second casing body, the first casing body and the second casing body are provided with accessory installation positions used for installing engine accessories, and the accessory installation positions are provided with reversing sealing structures. The reversing sealing structure comprises a plurality of attaching sealing faces which are connected in sequence and arranged in an included angle mode, and the engine accessories are jointly clamped through the attaching sealing faces so as to be sealed. The accessory mounting position comprises a lubricating oil pump mounting position arranged on the first casing body, and a fuel oil pump mounting position and an oil filter unit mounting position which are arranged on the second casing body, and the fuel oil pump mounting position is communicated with the oil filter unit mounting position through a fuel oil high-pressure pipeline and a fuel oil low-pressure pipeline; the lubricating oil pump installation position and the oil filter unit installation position are communicated through a lubricating oil pipeline, and the lubricating oil pipeline, the fuel oil low-pressure pipeline and the fuel oil high-pressure pipeline are sequentially arranged in the flame direction away from the expected engine fire behavior. The sealing effect and the fireproof performance can be greatly improved.

The invention relates to the technical field of engine fuel oil, in particular to a novel fuel oil evaporation system which comprises an engine, an air inlet channel, a fuel oil tank and a carbon tank, a fuel oil pump and a dumping valve are arranged on the fuel oil tank, an adsorption opening and a desorption opening are formed in the carbon tank, the fuel oil pump is connected with the air inlet channel, and the dumping valve is connected with the adsorption opening. A one-way valve is arranged between the air inlet channel and the carbon tank, an inlet of the one-way valve is connected with the adsorption port, and an outlet of the one-way valve is connected with the air inlet channel; a two-way valve is arranged between the fuel tank and the carbon tank, an inlet of the two-way valve is connected with the dumping valve, and an outlet of the two-way valve is connected with the adsorption opening. The gasoline engine has the advantages that waste and pollution caused by direct emission of fuel steam into air are reduced, cost is reduced, the structure is simplified, and the gasoline engine is suitable for a general gasoline generator set.

Disclosed in the present invention is an integrated reforming power generation test system having wide-range fuel adaptability, comprising a fuel supply subsystem, a catalytic reforming subsystem, a hydrogen purification subsystem, a power generation subsystem, and a test monitoring subsystem. A fuel pump and a fuel delivery pump are connected to a water-gas shift reactor by means of an evaporator and a reformer, the water-gas shift reactor is connected to a pressure swing adsorption device by means of a first gas-liquid separator, the pressure swing adsorption device is connected to a fuel cell stack by means of a hydrogen buffer tank, and a gas chromatograph is connected to the reformer by means of a third gas-liquid separator and to the water-gas shift reactor by means of a second gas-liquid separator. By using a variety of fuel resources to produce electricity, the present invention breaks through the limitation of the scope of traditional single-fuel reforming power generation systems, ensures the reliability of electricity supply, gets rid of the dependence on specific fuels, enhances regional energy safety, and improves the flexibility of energy supply.

The utility model provides a unilateral support horizontal fuel pump assembly, which is characterized by comprising a pump body mounting seat, a pump body, a fuel pump body, a fuel pump body, a fuel pump body and a fuel pump body, the fuel pump is mounted on the pump body mounting seat; the supporting frame is movably connected to the side face of the pump body mounting base; the flange is located above the supporting frame and is fixedly connected with the supporting frame through a supporting rod; the fuel pump is connected with an oil suction pipeline and an oil outlet pipeline, the oil outlet pipeline is connected with the flange, the oil suction pipeline is arranged on the pump body supporting seat and matched with the sliding guide groove through a supporting frame, and the supporting frame slides along the sliding guide groove during installation so that the supporting frame and the pump body installation seat can be approximately horizontal. At the moment, the fuel pump is integrally installed in the ship body, and the fuel pump assembly of the structure can be smoothly installed in the fuel tank.

A retrofit gas turbine engine includes a compressor, a combustor and a turbine. A tie shaft is connected to rotate by the turbine, and provide rotational drive into a gearbox. At least one fuel pump is connected to be driven by the gearbox. The at least one fuel pump delivers fuel downstream toward the combustor, and also has a return line. An added accessory turbine is positioned on the return line, and drives an added accessory which has been retrofit added to an existing gas turbine engine. A method is also disclosed.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a fuel cell stack auxiliary power unit (APU) and a first tank arranged to store liquid hydrogen with an ullage. A first fuel line includes a first pump and a first vaporiser and transports hydrogen from the first tank to combustion apparatus of the engine during operation of the propulsion system. A second fuel line includes a second fuel pump and a second vaporiser and transports hydrogen from the first tank to the fuel cell stack APU. A duct connects the second fuel line at a position thereon between the second vaporiser and the fuel cell stack to the ullage of the first tank, providing for pressure in the first tank to be maintained therein as liquid hydrogen within the first tank is depleted, thus avoiding cavitation of liquid hydrogen within the first fuel pump.

A method of operating a gas turbine engine of an aircraft, the gas turbine engine comprising: an engine core comprising a turbine, a compressor, a combustion chamber arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan arranged upstream of the engine core; a fan shaft; at least one bearing arranged to support the fan shaft; at least one auxiliary system arranged to consume a portion of the fuel; an oil circulation system arranged to supply oil to the at least one bearing; and a heat exchange system comprising: a primary fuel-to-oil heat exchanger through which the oil in the oil circulation system and at least substantially all of the fuel flow flow, such that heat is transferred between the oil and the fuel;and a secondary fuel-to-oil heat exchanger through which the oil in the oil circulation system and a portion of the fuel flow, such that heat is transferred between the oil and the fuel, wherein the secondary fuel-to-oil heat exchanger is arranged to supply fuel to the at least one auxiliary system; and a fuel pump arranged to pump the fuel, wherein the fuel pump is arranged along a fuel flow path downstream of the primary fuel-to-oil heat exchanger and upstream of the secondary fuel-to-oil heat exchanger; the method further comprising controlling the heat exchange system such that, under cruise conditions, the fuel temperature upon exiting the secondary heat exchanger is in the range of 120°C to 200°C.

A brushless motor fuel pump with a built-in controller, comprising a control unit, a brushless motor and a fuel pump connected in sequence. The control unit includes an oil outlet cover, a controller, a heat conducting pad, a mounting bracket and a metal heat sink. The mounting bracket is fixedly installed on the upper end of the brushless motor. A circulation cavity for the outflow of oil fluid is provided between the mounting bracket and the upper end of the brushless motor. The circulation cavity, the brushless motor and the fuel pump are connected in sequence. The oil outlet cover is fixedly connected to the upper end of the mounting bracket, and the oil outlet cover is provided with an oil outlet communicating with the circulation cavity. The mounting bracket and the oil outlet cover are hermetically connected to form a sealed cavity for installing the controller. The controller, the heat conducting pad and the metal heat sink are connected in sequence from top to bottom. The lower part of the metal heat sink is hermetically installed in a mounting hole provided in the mounting bracket, and the metal heat sink passes through the mounting hole and is exposed in the circulation cavity.

An electric GDI pump is configured to allow fuel being pumped to cool the electric motor and associated motor control / drive circuit, and cool and lubricate a drive region of a high-pressure pump before passing through an inlet check valve of the high-pressure pump. The rotational speed of an electric GDI pump is de-coupled from the rotational speed of the internal combustion engine. In such a fuel supply system, the quantity of fuel pressurized can be regulated by changing the rotational speed of the electric GDI pump. According to aspects of the disclosure an electric GDI pump is driven by a variable speed direct current motor having a motor housing with a fuel inlet and a motor drive shaft connected to a rotor. The electric GDI pump may incorporate a low-pressure pump driven by one end of the drive shaft and an eccentric drive driven by an opposite end of the drive shaft.

The invention relates to the technical field of generator fuel pump control, in particular to an energy-saving generator fuel pump optimization method and system. Comprises: continuously collecting operation parameters of a generator system, and determining whether the generator system is in a stable operation condition; after the stable operation working condition is judged, perturbation testing is executed, and the actual output pressure and the actual fuel flow of the fuel pump are obtained; calculating the performance deviation of the fuel pump, and carrying out trend analysis to identify continuous performance drift; when the trend analysis shows that continuous performance drifting exists, self-adaptive correction is conducted on the fuel pump control basis to obtain the corrected fuel pump control basis; and the corrected fuel pump control basis is applied to control operation of the fuel pump. The problems that hidden energy consumption is increased and equipment failure risks are caused when an existing generator fuel pump control system is in the face of tiny changes of fuel physical attributes and gradual degradation of the performance of a fuel pump are solved.

A method for detecting fuel fraud when refueling a vehicle at a filling station comprises obtaining, in conjunction with a current refueling operation in which the vehicle is refueled at the filling station, current refueling information (66), determining if there is a mismatch between the obtained current refueling information (66) and historical refueling information (74) which is based on a plurality of past refueling operations in which comparable vehicles were refueled, and raising a potential fraud warning (80) based at least in part on a determined mismatch. The current refueling information comprises at least: first information (70.1) indicating a distance the vehicle (30) traveled since at least a previous refueling operation, second information (70.2) indicating a duration and / or progress of the current refueling operation, and third information (70.3) indicating an amount of fuel dispensed by a fuel pump (12) in the current refueling operation. One or more machine-readable media, a server installation (28) and a system are adapted to perform corresponding operations or cause corresponding operations to be performed.

An in-tank fuel pump assembly and mounting system is disclosed which may be configured for mounting inside a fuel tank. The assembly includes a pump housing, pump mounted to the housing, and pressure relief valve. The housing may comprise upper and lower pump housing units coupled together. The upper housing unit is configured for mounting to a tank opening, which in one implementation may be the fuel fill opening. The lower housing unit extends into the tank to approximately the bottom of the tank. A fuel fill fluid pathway is created through the housing for adding fuel to the tank while the pump assembly remains in situ. The upper housing unit may include a removable fuel cap. The pump housing may include an integral vapor trap.