Arrangement for multi-stage heat pump assembly
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IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F25D-009/00
F28C-001/00
F04B-025/00
F04B-003/00
출원번호
US-0311620
(2001-02-28)
우선권정보
IL-136921(2000-06-22)
국제출원번호
PCT/IL01/000186
(2001-02-28)
§371/§102 date
20030911
(20030911)
국제공개번호
WO01/098665
(2001-12-27)
발명자
/ 주소
Ophir,Avraham
Rojanskiy,Henrikh
Kanievski,Arie
출원인 / 주소
I.D.E. Technologies, Ltd.
대리인 / 주소
Birch, Stewart, Kolasch &
인용정보
피인용 횟수 :
6인용 특허 :
5
초록▼
A gasdynamic arrangement for a multi-stage centrifugal turbomachine, such as a two-stage compressor, comprising two coaxial impellers assembled on a common shaft with axial intake ports and radial peripheral discharge zones, the intake ports of the two impellers preferably pointing away from each ot
A gasdynamic arrangement for a multi-stage centrifugal turbomachine, such as a two-stage compressor, comprising two coaxial impellers assembled on a common shaft with axial intake ports and radial peripheral discharge zones, the intake ports of the two impellers preferably pointing away from each other; a cylindrical vessel concentrically housing the impellers and the intake duct; a partition wall between the two impellers having a first and a second group of apertures; a first array of curved ducts conveying the flow from the first impeller discharge zone to the first group of apertures in the partition wall, the flow further passing through a chamber in the vessel to the intake port of the second impeller, and a second array of curved ducts conveying the flow from the second impeller discharge zone to the second group of apertures in the partition wall, the flow further going to the discharge port, the two flows bypassing each other in opposing directions at the partition wall.
대표청구항▼
What is claimed is: 1. Gasdynamic arrangement for a multi-stage centrifugal turbomachine having an intake duct (16) and a discharge port ( 38), and comprising: a) a first impeller (26) with axial intake port and radial peripheral discharge zone, said axial intake port being in fluid communication w
What is claimed is: 1. Gasdynamic arrangement for a multi-stage centrifugal turbomachine having an intake duct (16) and a discharge port ( 38), and comprising: a) a first impeller (26) with axial intake port and radial peripheral discharge zone, said axial intake port being in fluid communication with said intake duct; b) a second impeller (29) with axial intake port and radial peripheral discharge zone, said second impeller disposed coaxially with said first impeller, the two impellers being located at two sides of an imaginary plane crossing their common axis; c) a first means for conducting the flow from the peripheral discharge zone of the first impeller to the intake port of the second impeller along a first flow path (28, C2) including a plurality of first curved ducts (28) in axisymmetric arrangement; d) a second means for conducting the flow from the peripheral discharge zone of the second impeller towards said discharge port of the machine along a second flow path (37, C1) including a plurality of second curved ducts (37) in axisymmetric arrangement; wherein said first and said second flow paths (28, 37) leave the respective peripheral discharge zones bending gradually towards said imaginary plane, said first and said second flow paths cross said imaginary plane in opposite directions and, after crossing said imaginary plane, the two flow paths lie entirely at different sides of the imaginary plane, and wherein said first and said second curved ducts (28, 37) have diffuser shape with cross-section area increasing from the impeller periphery discharge zone to said imaginary plane. 2. Gasdynamic arrangement according to claim 1, comprising a partition wall (24) between said impellers (26, 29), said wall lying substantially in said imaginary plane and having a plurality of first apertures (P1) and a plurality of second apertures (P2), wherein: a) said plurality of first curved ducts (28) connects the peripheral discharge zone of the first impeller (26) to said plurality of first apertures P1, and said first means for conducting the flow further comprises a first outer shell (C1) defining, together with said partition wall (24), a chamber conducting the flow from said plurality of first apertures P1 to the intake of the second impeller (29), said chamber at least partially encompassing said second impeller; b) said plurality of second curved ducts (37) connects the peripheral discharge zone of the second impeller (29) to said plurality of second apertures (P2), and said second means for conducting the flow further comprises a second outer shell (C2) defining, together with said partition wall (24), a chamber conducting the flow from said plurality of second apertures (P2) towards said discharge port (38). 3. Gasdynamic arrangement according to claim 2, wherein: a) said plurality of first curved ducts (28) are arranged in a first crown array around the first impeller (26); b) said plurality of second curved ducts (37) are arranged in a second crown array around the second impeller (29); c) said plurality of first apertures (P1) on the partition wall (24) connected to the plurality of first curved ducts (28) are positioned in alternating pattern between said plurality of second apertures (P2) connected to the plurality of second curved ducts (37). 4. Gasdynamic arrangement according to claim 2, wherein said turbomachine is encased in a substantially integral axisymmetric shell (C) coaxial with said impellers (26, 29), said first and second outer shells (C1, C2) being part of said integral shell. 5. Gasdynamic arrangement according to claim 4, wherein said discharge port (38) of the turbomachine is located substantially at the same side of said integral shell (C) as the inlet of said intake duct (16). 6. Gasdynamic arrangement according to claim 4, wherein said integral axisymmetric shell (C) is formed as a cylinder with diameter approximately twice the diameter of the impellers. 7. Gasdynamic arrangement for a multi-stage centrifugal turbomachine according to claim 2, wherein said fluid communication between the intake port of the first impeller (26) and the intake duct (16) is performed via at least one additional stage in the following way: a) an additional impeller (48) having an axial intake port and a radial peripheral discharge zone is disposed coaxially between said intake duct and said intake port of the first impeller, the intake port of the additional impeller being at the side of and connected to the intake duct (16); b) an additional partition wall (54) with a plurality of first apertures (P1') and a plurality of second apertures (P 2') is situated between the additional impeller (48) and the intake port of the first impeller in a plane perpendicular to the axis of the impellers; c) an additional plurality of curved ducts (57) is added to connect the peripheral discharge zone of the additional impeller to said plurality of first apertures (P1') on the additional partition wall (54); d) said plurality of second curved ducts (37) connecting the peripheral discharge zone of the second impeller (29 ) to the plurality of second apertures (P2) in the existing partition wall (24) is extended to the plurality of second apertures (P2') in the additional partition wall (54). 8. A multi-stage centrifugal compressor having the gasdynamic arrangement for multi-stage turbomachine according to claim 1. 9. A two-stage centrifugal compressor according to claim 8, wherein said first and second impeller are mounted on a common impeller shaft (40) adapted to be driven by one motor (10). 10. A two-stage centrifugal compressor according to claim 9, wherein said impeller shaft (40) is supported by one bearing house (42) disposed between said first and second impellers. 11. A two-stage centrifugal compressor according to claim 9, wherein said common impeller shaft is the shaft of said motor, said impellers being mounted on the two ends of said shaft. 12. A heat pump comprising a two-stage centrifugal compressor according to claim 8 with an intake duct (16), a discharge port (38), and a driving motor (10), the heat pump further comprising an evaporation chamber (A), in fluid connection with said intake duct, and a condenser chamber (B), in fluid connection with said discharge port, and an integral axisymmetric housing (11) coaxial with the compressor, accommodating all elements of said pump or all elements except for the driving motor. 13. A heat pump according to claim 12, wherein said integral housing (11) is divided into chambers by transverse separation walls (12, 13), said chambers being arranged in the following order along the axis of the housing: a) evaporator chamber (A), b) condenser chamber (B) surrounding said intake duct ( 16), c) compressor chamber (C), the evaporator chamber (A) being opened towards the intake duct (16), the discharge port (38) of said two-stage compressor being opened towards said condenser chamber (B). 14. A heat pump according to claim 13, wherein said heat pump comprises further: means (15) to feed water into said evaporator chamber; means (22) to spray water into said condenser chamber; means (45) to pump out chilled water; means (44) to pump out heated cooling water; and at least one of the following devices: means (33) for mist elimination situated prior to flow entry into impeller intake ports; means (31) for intercooling the compressed gas situated in the flow path between said impellers. 15. A heat pump according to claim 12, wherein said condenser chamber (B) is arranged as an annular chamber around said intake duct ( 16), said discharge port (38) opening into said condenser chamber.
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이 특허에 인용된 특허 (5)
Ophir Avraham (Herzliya ILX) Olomutzki David (Kfar-Saba ILX) Koren Abraham (Holon ILX) Kanevski Arie (Kfar-Saba ILX), Centrifugal compressor and heat pump comprising.
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