[특허]Pump and pump control circuit apparatus and method

SHURflo Pump Manufacturing Company, Inc.

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Pump and pump control circuit apparatus and method

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F04B-049/06
미국특허분류(USC)	417/044.1; 417/053; 417/423.14; 417/559
출원번호	US-0994378 (2001-11-26)
발명자 / 주소	Meza, Humberto V. Wang, Congxiao Calvin
출원인 / 주소	SHURflo Pump Manufacturing Company, Inc.
대리인 / 주소	Michael Best & Friedrich LLP
인용정보	피인용 횟수 : 89 인용 특허 : 67

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A method and apparatus for a pump and a pump control system. The apparatus includes pistons integrally formed in a diaphragm and coupled to the diaphragm by convolutes. The convolutes have a bottom surface angled with respect to a top surface of the pistons. The apparatus also includes an outlet port positioned tangentially with respect to the perimeter of an outlet chamber. The apparatus further includes a non-mechanical pressure sensor coupled to a pump control system. For the method of the invention, the microcontroller provides a pulse-width modulation control signal to an output power stage in order to selectively control the power provided to the pump. The control signal is based on the pressure within the pump, the current being provided to the pump, and the voltage level of the battery. hesion layer is applied between the surface of the blades and the coating. 14. The low-pressure turbine according to claim 1, wherein: the coating is applied to the surfaces of the stationary and the rotating blades of the low-pressure turbine. rther comprising: sound insulating material in the inlet and outlet. 13. An inner deflector ring for use in a bypass port compressor having an axial inlet defining a central channel and an annular channel disposed concentrically therearound, a compressor wheel disposed within the compressor, and an aperture providing communication between compressor wheel and the annular channel, the inner deflector ring comprising: a first substantially radially extending surface, for obstructing flow along the annular channel, and a second substantially axially extending surface. 14. An inner deflector ring as defined in claim 13 further comprising: a third axially extending surface extending along the annular channel and separated from the first axially extending surface by the second radially extending surface, which is disposed therebetween. 15. A turbocharger system having a noise reduction device comprising: a bypass port compressor having a housing, a concentric inner radial wall and outer radial wall collectively defining the compressor inlet, the inner radial wall circumscribing a central channel, and an annular channel interposed between the outer radial wall and the inner radial wall, the annular channel being disposed concentrically around the central channel, a compressor outlet, a compressor wheel having a plurality of vanes, the wheel located between the inlet and outlet and in communication with both the central and annular channels; and an inner deflector disposed within the annular channel, having a first surface extending radially across the annular channel, and a second surface extending axially along the annular channel, to partially obstruct flow into and out of the annular channel. 16. A turbocharger system as defined in claim 15 further comprising: a noise suppressor disposed within the compressor inlet, wherein the noise suppressor is coupled to an inner surface of the outer radial wall. 17. A turbocharger system as defined in claim 16 wherein: the noise suppressor is cylindrical. 18. A turbocharger system as defined in claim 17 wherein: the outer diameter of the noise suppressor is greater than the outer diameter of the annular channel. 19. A turbocharger system as defined in claim 17 wherein: the inner diameter of the noise suppressor is less than the inner diameter of the annular channel. 20. A turbocharger system as defined in claim 15 wherein: the noise suppressor is substantially "C" shaped in cross-section. 21. A turbocharger system as defined in claim 15 wherein: the noise suppressor is substantially "J" shaped in cross-section. 22. A turbocharger system as defined in claim 15 wherein: the noise suppressor is substantially "L" shaped in cross-section. m is partially accommodated by the slot and extends outwardly beyond the sidewall. A retaining mechanism is disposed in the bore. The retaining mechanism acts on the cam when the cam is in the unlocking condition and moves into the slot when the cam is in the locking condition thereby to inhibit the cam from returning to the unlocking condition. wheel for supporting the turbine shaft for rotation; a seal about the turbine shaft and upstream from the bearing for sealing the upstream side of the bearing and having an upstream side and a downstream side having a bearing seal downstream fluid pressure; and a conduit extending from the upstream turbine wheel side to the seal upstream side so that the seal upstream side has a higher pressure than the seal downstream side. 13. The air turbine starter of claim 12 wherein the seal is a first seal and further comprising a second seal upstream from the first seal and defining a cavity into which the conduit opens. 14. The air turbine starter of claim 12 wherein the conduit extends through the turbine wheel. 15. The air turbine starter of claim 14 wherein conduit extends into the turbine wheel along an axis and includes a radially-extending portion. 16. The air turbine starter of claim 15 wherein the radially-extending portion extends outwardly to an edge of the turbine wheel and on the downstream side of the turbine wheel. 17. The air turbine starter of claim 16 wherein the conduit includes a first portion extending along the turbine wheel axis having a first cross-sectional area and wherein the radially-extending portion includes a second cross-sectional area less than the first cross-sectional area. 18. The air turbine starter of claim 12 wherein the conduit includes means extending from the upstream side of the turbine wheel through the turbine wheel to the downstream side of the turbine wheel. 19. An air turbine starter comprising: a housing defining an inlet at a first pressure, an outlet at a second pressure less than the first pressure, and a flow path between the inlet and the outlet for conveying a flow of air therebetween; a turbine wheel having vanes disposed in the flow path and wherein the turbine wheel is supported by a turbine shaft supported within the housing by at least one lubricated bearing and producing turbine shaft power, wherein the turbine wheel has an upstream side at a third pressure and a downstream side at a fourth pressure less than the third pressure; an output shaft for transmitting the shaft power externally of the starter; a gear train coupling the turbine with the output shaft; a first seal adjacent the at least one lubricated bearing and between the bearing and the turbine wheel; and a pressure seal spaced from the first seal toward the turbine wheel and having a turbine wheel side and a first seal side for maintaining a pressure difference across the pressure seal; and a second air flow path extending from the upstream side of the turbine wheel at the third pressure to a point between the pressure seal and the first seal. 20. A turbine comprising: a turbine inlet; a turbine wheel housing having a wall upstream from the turbine inlet; a turbine wheel having an upstream side on a side of the housing opposite the turbine inlet and a downstream side; a shaft for supporting the turbine wheel and extending downstream from the turbine wheel; a bearing about the turbine shaft for supporting the turbine shaft for rotation; a first seal about the turbine shaft having an upstream side and a downstream side and upstream from the bearing for sealing an upstream side of the bearing and wherein the bearing has a fluid pressure during normal operation on the upstream side; a second seal upstream from the first seal and defining a region between the first and second seals; a conduit through the turbine wheel for supplying fluid to the region between the first and second seals so that a positive pressure differential is created from the upstream side of the first seal to the downstream side of the first seal. 21. The turbine of claim 20 wherein the second seal upstream from the first seal is an air seal and wherein the conduit includes a first wall defining a first bore coaxial with a central axis of the turbine wheel extending from the upstream side of the turbine wheel along the c entral axis, and a second wall defining a second bore extending substantially radially from the first bore to an outer surface of the turbine wheel on the downstream side of the turbine wheel. 22. The turbine of claim 21 wherein the first and second bores have respective cross-sectional areas wherein the second bore cross-sectional area is less than the first bore cross-sectional area. 23. The turbine of claim of 20 wherein the second seal is one of a multiple knife labyrinth, a lip seal, a clearance floating ring seal, an arch bound floating ring seal, a short static bushing, a long static bushing, or a wind back, an outside or inside contacting piston ring, a floating free ring, a brush seal, and a face seal. 24. A turbine comprising: a turbine assembly having a turbine wheel supported on a turbine shaft and wherein the turbine wheel includes an upstream side and a downstream side; a seal for sealing around the turbine shaft downstream from the turbine wheel and having an upstream side and a downstream side, wherein a fluid pressure exists on the upstream side of the seal; and a fluid conduit extending from the upstream side of the turbine wheel to the downstream side of the turbine wheel and to the upstream side of the seal so that the fluid pressure at the upstream side of the seal is greater than the fluid pressure on the downstream side of the seal so that there is a positive pressure differential from the upstream to the downstream side of the seal. 25. A method for creating a pressure differential across a seal, the method comprising the steps of: forming a first bore in a turbine wheel; forming a second bore in the turbine wheel intersecting the first bore wherein the first bore opens on an upstream side of the turbine wheel at a first pressure and the second bore opens on a downstream side of the turbine wheel; supporting the turbine wheel within a housing through a set of bearings about a turbine wheel shaft; providing a first seal for the bearings between the bearings and the turbine wheel; and providing a second seal on a side of the second bore opposite the first seal wherein the second seal includes a first side closer to the second bore and a second side farther from the second bore and wherein the second side is exposed to a fluid pressure less than the first pressure. 26. The method of claim 25 wherein the step of forming the first bore includes the step of forming the first bore coaxial with an axis of the turbine wheel. 27. The method of claim 25 further comprising the step of creating a cavity between the first seal and the second seal. 28. The method of claim 25 wherein the step of providing a second seal includes the step of providing one of a multiple knife labyrinth, a lip seal, a clearance floating ring seal, an arch bound floating ring seal, a short static bushing, a long static bushing, or a wind back, an outside or inside contacting piston ring, a floating free ring, a brush seal, and a face seal. 29. A kit for installing an air-to-air seal assembly in an air turbine starter, the kit comprising: a turbine wheel having a first face on a first side of the turbine wheel and a hub on a side of the turbine wheel different from the first side and having a hub surface between the turbine wheel and a turbine shaft; and a first wall in the turbine wheel and opening at the first face and defining a first channel for allowing air to pass into the first channel; and a second wall in the hub defining a second channel for allowing air to pass from the first channel to the surface of the hub. 30. The kit of claim 29 wherein the turbine wheel includes a center portion on the first face and wherein the first channel is formed in the center portion of the first face of the turbine wheel. 31. The kit of claim 29 wherein the turbine wheel includes a central axis and wherein the first channel is formed coaxial with the central axis. 32. The kit of claim 29 wherein the second channel is formed in

이 특허에 인용된 특허 (67)

이 특허를 인용한 특허 피인용횟수: 89

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Pump and pump control circuit apparatus and method

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Pump and pump control circuit apparatus and method

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이 특허에 인용된 특허 (67)

이 특허를 인용한 특허 피인용횟수: 89

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