中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

36 records (took 0.027 seconds)

    CENTRIFUGAL AIR FLOW CONTROL
    21.
    发明专利
    CENTRIFUGAL AIR FLOW CONTROL 未知

    公开(公告)号：CA2364321C

    公开(公告)日：2008-06-10

    申请号：CA2364321

    申请日：2000-02-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORBER PETER F ,  LORD WESLEY K

    IPC: F15D1/12 ,  B64C11/18 ,  B64C21/02 ,  B64C21/04 ,  B64C27/467 ,  F01D5/14

    Abstract: Blades, including helicopter rotor blades, gas turbine engine fan blades, ai r moving machinery fan blades, and the like, have an air inlet near the hub of the blade, which may be on the pressure side of the blade and/or near the leading edge or trailing edge nearer the tip of the blades, with an air plenum between the air inlet and the slots, whereby air is forced into the inlet, through the plenum and out of the slots into the flow adjacent the blades. The slots may be through the suction surface of the blade, typically near the boundary layer separation point, so that air flowing out of the slots into the boundary lay er of suction surface of the blade, thereby delay or prevent the onset of the boundary layer separation, or to reduce supersonic shock. The inlet may be near the trailing edge of the blade, near the root, adjacent to the air inlet of the core of a jet engine, to suction off air an d reduce fan wake blockage at the core inlet. The slots may be through the pressure surface adjacent the blade tip edge of fan blades to reduce blade tip leakage effects.

    22.
    发明专利
    未知

    公开(公告)号：DE69934757D1

    公开(公告)日：2007-02-22

    申请号：DE69934757

    申请日：1999-11-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZYSMAN STEVEN H ,  KOHLENBERG GREGORY A ,  LORD WESLEY K

    IPC: F02C7/045 ,  F02K1/46 ,  F02K1/38 ,  F02K1/48 ,  F02K3/02

    Abstract: The jet noise suppressor includes a nozzle (20; 30), having an arrangement thereon of trapezoidal tabs (40) disposed on the downstream end of the nozzle (20; 30), the tabs (40) having a length (L) and the angular offset with respect to the engine flow such that mixing occurs primarily at the interface of the engine flow and the ambient air. In addition, various construction details are developed for the tabs including tabs that are trapezoidal with tapered sides such that the tabs minimize adverse impact to engine performance.

    23.
    发明专利
    未知

    公开(公告)号：DE69625005T2

    公开(公告)日：2003-04-10

    申请号：DE69625005

    申请日：1996-09-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZYSMAN STEVEN H ,  LORD WESLEY K ,  BARBER THOMAS J

    IPC: F02K1/40 ,  F02K1/38 ,  F02K1/46 ,  F02K1/48 ,  F02K3/06

    Abstract: A lobed mixer (7) has major and minor lobes (8,9). The major lobes increase in both height and width in the downstream axial direction. Each major lobe (8) has two minor lobes (9) positioned on its radially outer surface located downstream of the beginning of the major lobe. The radial depth of the minor lobes increases with downstream axial distance but is never greater than the depth of the major lobes. Each of the chutes (11) formed between the minor lobes introduces an additional stream of cold, low velocity fan flow into the hot, high velocity core flow to improve the uniformity of mixing. The double lobed mixer decreases acoustic intensity while having little or no effect on engine performance.

    24.
    发明专利
    未知

    公开(公告)号：DE69625005D1

    公开(公告)日：2003-01-09

    申请号：DE69625005

    申请日：1996-09-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZYSMAN STEVEN H ,  LORD WESLEY K ,  BARBER THOMAS J

    IPC: F02K1/40 ,  F02K1/38 ,  F02K1/46 ,  F02K1/48 ,  F02K3/06

    Abstract: A lobed mixer (7) has major and minor lobes (8,9). The major lobes increase in both height and width in the downstream axial direction. Each major lobe (8) has two minor lobes (9) positioned on its radially outer surface located downstream of the beginning of the major lobe. The radial depth of the minor lobes increases with downstream axial distance but is never greater than the depth of the major lobes. Each of the chutes (11) formed between the minor lobes introduces an additional stream of cold, low velocity fan flow into the hot, high velocity core flow to improve the uniformity of mixing. The double lobed mixer decreases acoustic intensity while having little or no effect on engine performance.

    Centrifugal air flow control
    25.
    发明专利
    Centrifugal air flow control 未知

    公开(公告)号：AU3504300A

    公开(公告)日：2000-09-14

    申请号：AU3504300

    申请日：2000-02-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORBER PETER F ,  LORD WESLEY K

    IPC: B64C11/18 ,  B64C21/02 ,  B64C27/467 ,  F01D5/14 ,  F15D1/12 ,  B64C21/04

    Abstract: Blades, including helicopter rotor blades, gas turbine engine fan blades, air moving machinery fan blades, and the like, have an air inlet near the hub of the blade, which may be on the pressure side of the blade and/or near the leading edge or trailing edge nearer the tip of the blades, with an air plenum between the air inlet and the slots, whereby air is forced into the inlet, through the plenum and out of the slots into the flow adjacent the blades. The slots may be through the suction surface of the blade, typically near the boundary layer separation point, so that air flowing out of the slots into the boundary layer of the suction surface of the blade, thereby delay or prevent the onset of boundary layer separation, or to reduce supersonic shock. The inlet may be near the trailing edge of the blade, near the root, adjacent to the air inlet of the core of a jet engine, to suction off air and reduce fan wake blockage at the core inlet. The slots may be through the pressure surface adjacent the blade tip edge of fan blades to reduce blade tip leakage effects.

Patent Agency Ranking