Abstract:
An inducer includes a hub having an inlet end and an outlet end. At least one full size blade has an inner edge is affixed to the hub and an outer edge. This full size blade extends rearwardly from the inlet end in a helical configuration. A partial shroud encloses a first length of the full size blade outer edge adjacent the inlet end. A second length of the full size blade outer edge that is adjacent to the outlet end is free of the partial shroud. It is within the scope of the disclosure to include short blades symmetrically offset from the two full size blades. These short blades have a short blade inner end affixed to the partial shroud and a short blade outer end extending from the partial shroud towards the hub, but terminating prior to reaching the hub.

Description:
CROSS REFERENCE TO RELATED APPLICATION(S) 
       [0001]    N.A. 
       U.S. GOVERNMENT RIGHTS 
       [0002]    N.A. 
       BACKGROUND 
       [0003]    1. Field 
         [0004]    The disclosure herein relates to an inducer employed to increase the pressure of a liquid introduced to a pump. More particularly, the inducer increases the pressure of a liquid propellant being pumped to the combustion chamber of a rocket engine. 
         [0005]    2. Description of the Related Art 
         [0006]    Liquid fuel rocket engines typically include tanks containing a liquid oxidizer, such as liquid oxygen, and a liquid fuel, such as liquid hydrogen, collectively called propellants. To reduce the thickness of the tanks and their associated weight, the liquid propellants are usually at a relatively low pressure. The liquid propellants are pumped to a combustion chamber and then ignited to generate thrust. To achieve sufficient thrust, the liquid propellants must be sufficiently pressurized prior to introduction to the combustion chamber. A pump, such as a turbopump, is used to pressurize the liquid propellants. As a first step, an inducer may be located between the propellant tanks and the turbopump to produce an initial pressure increase. 
         [0007]    The inducer is an axial flow pumping device, typically a first element of low weight, high performance pumps, for use in liquid propulsion rocket engines. The inducer receives the liquid propellant at a very low inlet pressure and provides sufficient discharge pressure for the next pump stage, usually a radial impeller, to operate safely at high shaft speeds. The inducer must achieve satisfactory discharge pressure at the inducer exit with extremely low pressure at the inlet. The inducer includes a number of rapidly spinning blades to draw the liquid propellant through the inducer. Vortices tend to form on the tips of the blades causing cavitation damage to the blades and a variety of vibrations associated with vortex cavitation instabilities that may be detrimental to the engine operability or life. 
         [0008]    It is known that enclosing the tips of the blades in a shroud eliminates the formation of vortices. For example, U.S. Pat. No. 4,642,023 entitled “Vented Shrouded Inducer,” discloses a shroud with a series of holes that allows counterflowing fluid around the outside of the shroud to flow back into the impeller. U.S. Pat. No. 7,070,388, entitled “Inducer with Shrouded Rotor for High Speed Applications,” discloses an inducer rotor with rotor blades terminating at a shroud. The shroud has a variable thickness both to reduce weight and to maintain a uniform gap between the shroud and a housing wall during high speed rotation. U.S. Pat. No. 7,931,441, entitled “Inducer with Tip Shroud and Turbine Blades,” discloses an inducer with two sets of blades arranged axially one after the other. The upstream blades are full size and the downstream blades are half size. The downstream half size blade tips are enclosed in a shroud. 
         [0009]    U.S. Pat. Nos. 4,642,023; 7,070,388 and 7,931,441 are incorporated by reference herein in their entireties. 
         [0010]    At high rotating speeds, even shrouded blades are subject to a manifestation of cavitation-related hydrodynamic phenomena, including the type referred to as alternate blade cavitation. Alternate blade cavitation manifests as long and short vapor cavities on alternate blades. When there are only two blades, alternate blade cavitation is inherently asymmetric, with a short cavity on one blade and a long cavity on the other blade, resulting in radial load imbalance. A symmetric pattern is only possible with an even number of at least four inducer blades (e.g. 6 or 8 blades also achieve symmetry). Four bladed inducers are utilized in many present day rocket engines. In a four bladed inducer, alternate blade cavitation is characterized by a stable pattern of two large cavities on one opposing pair of blades and two small cavities on the other pair of opposing blades. Such stable patterns result in low radial loads beneficial to bearing life and do not generate traveling pressure instabilities or adverse system vibrations. 
         [0011]    However, ultra high suction capability requires a very low inlet flow coefficient (very low ratio of axial inlet velocity to blade tip speed), which in turn requires very low blade angles with respect to the tangential direction, producing a high degree of fluid flow blockage. Higher blade counts exacerbate the blockage problem at low blade angles. 
         [0012]    There remains a need for an inducer having the fluid flow capacity of a two or three blade configuration and the cavitation stability of a four blade configuration. 
       BRIEF SUMMARY 
       [0013]    In accordance with a first embodiment of the disclosure, an inducer includes a hub having an inlet end and an outlet end. At least one full size blade has an inner edge affixed to the hub and an outer edge. This full size blade extends rearwardly from the inlet end in a helical configuration. A partial shroud encloses a first length of the full size blade outer edge adjacent the inlet end. A second length of the full size blade outer edge that is adjacent to the outlet end is free of the partial shroud. 
         [0014]    One feature of this embodiment is that the inducer has a low number of full size blades and preferably has two full size blades, offset by 180°, symmetrically disposed about the hub. 
         [0015]    Another feature of an inducer with the partial shroud embodiments is that, unlike a fully shrouded low flow-coefficient inducer, this inducer is machinable in one piece, which lowers fabrication cost and preserves dimensional accuracy. 
         [0016]    In accordance with a second embodiment, the inducer of the first embodiment further includes short blades symmetrically offset from the two full size blades. These short blades have a short blade inner end affixed to the partial shroud and a short blade outer end extending from the partial shroud towards the hub, but terminating prior to reaching the hub. 
         [0017]    Alternatives of this second embodiment include the short partial blades having an inner end affixed to the inducer hub and an outer end terminating before the radius of the full size blade is reached and where there are two sets of partial blades, one set attached to the hub and the other set attached to the shroud. 
         [0018]    The details of one or more embodiments of the invention are set forth in the accompanying drawings and the description below. Other features, objects and advantages of the invention will be apparent from the description and drawings, and from the claims. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0019]      FIG. 1  illustrates in cross-sectional representation a partially shrouded inducer in accordance with a first embodiment disclosed herein. 
           [0020]      FIG. 2A  is a frontal view of the inlet face of the inducer of  FIG. 1 . 
           [0021]      FIG. 2B  is a cross-sectional view of the full size blades of  FIG. 2A  at the leading edge showing the leading edge wedge angle. 
           [0022]      FIG. 3  is a side perspective view of the inducer of  FIG. 1  illustrating the helical shape of an inducer blade, although the blade angle can vary from the leading edge to the trailing edge. 
           [0023]      FIG. 4  is a frontal view of an inlet face of an inducer illustrating alternate blade cavitation. 
           [0024]      FIG. 5  is a frontal view of the inlet face of an inducer having both full blades and partial blades in accordance with a second embodiment disclosed herein. 
           [0025]      FIG. 6  is a frontal/side perspective view of the inducer of  FIG. 5 . 
           [0026]      FIG. 7  is a frontal view of the inlet face of an inducer having full blades and partial blades in accordance with a third embodiment disclosed herein. 
           [0027]      FIG. 8  is a frontal view of the inlet face of an inducer having full blades and two sets of partial blades in accordance with a fourth embodiment disclosed herein. 
           [0028]      FIG. 9  is a frontal view of the inlet face of an inducer having full blades and partial blades axially offset from the full blades in accordance with a fifth embodiment disclosed herein. 
       
    
    
       [0029]    Like reference numbers and designations in the various drawings indicate like elements. 
       DETAILED DESCRIPTION 
       [0030]      FIG. 1  illustrates a first embodiment of an inducer  10  having ultra-high suction performance effective to enable operation of an upper stage pump-fed engine at low inlet pressures and low pressure margins from propellant vapor pressure over a wide range of flowrates, thereby reducing the overall system weight and facilitating more complete propellant utilization. Inducer  10  has a cylindrical-symmetry hub  12  formed by either a straight line (resulting in a cylindrical or conical hub) or a polynomial. An upstream, inlet hub face  14  has a diameter, d 1 , that is from 30% to 50% the diameter, d 2 , of the tips  16  of full size inducer blades  18 . The inducer  10  terminates at a downstream, discharge hub face  20  that has a diameter, d 3 , that is equal to or larger than the diameter, d 1 , of the inlet hub face  14 . 
         [0031]    With reference to  FIG. 2A , the full size inducer blades  18  extend from the hub  12  to a partial shroud  22 . There are preferably at least two full size inducer blades  18 . To minimize fluid flow blockage, two or three full size inducer blades symmetrically disposed around the hub  12  are most preferred. The full size inducer blades are backwards swept at the hub  12  and forward swept at the tip  16 , resulting in the leading edge contour, also referred to as the “sweep,” that has a shape similar to the letter “C”. In a polar coordinate system, with Z being the axis of rotation, theta (Θ) being the blade wrap angle defined as positive in the direction of rotation, and zero theta being at the position where the leading edge of the blade meets the hub, blade sweep is the 0 position along the leading edge of the blade. Typically, a blade has forward sweep if the leading edge of the blade at the tip is at a positive Θ position. Inducer  10  has a variable sweep leading edge  68 . Typically, for a shrouded and forward swept inducer, the angular depth  69  of the minimum sweep is achieved between 5% and 50% span from the hub  12  and is between 0° and −45°. The forward-swept leading edge  68  controls the effective incidence angle distribution and limits the volume of incidence driven sheet cavitation. 
         [0032]    With reference to  FIG. 2B , when viewed along the Z axis, the full size inducer blade  18  has a leading edge wedge  72  profiled for cavitation control. Typically, the leading edge wedge angle, α, is between 3° and 7° in the R*Θ−Z plane. 
         [0033]    Referring to  FIGS. 1 and 3 , the partial shroud  22  is a variable axial length cylindrical shroud that encloses the tips  16  of the full size inducer blades  18  for a first axial length, L 1 , corresponding to about 180° wrap, that begins adjacent the inlet hub face  14  and extends towards the discharge hub face  20 , terminating prior to the end of the full size inducer blades  18 ′ such that a second length, L 2 , of the blades is free of the partial shroud  22  and has a blade tip diameter matching the outer diameter of the partial shroud. L 1  extending past the throat or terminating just before the throat is acceptable. The operating flow coefficient is between 0.02 and 0.05, the lowest practical range achievable when taking into account blade blockage of a two bladed inducer using existing material of construction. 
         [0034]    The full size inducer blades  18  have a blade length L 1 +L 2 , as determined by the total wrap angle at the tip  16 , effective to insure tip solidity of at least 1.5, where tip solidity is the ratio of the blade chord length along the tip and the circumferential spacing between blades at discharge. As illustrated in  FIG. 5 , in accordance with a second embodiment, short inducer blades  24  are symmetrically offset from the full size inducer blades  18 . 
         [0035]    Referring back to  FIG. 1 , the inducer  10  is mounted on a shaft  30  within a pump housing  28 , such as a turbopump used to transfer a liquid propellant to a combustion chamber of a rocket. A shaft  30  rotated, such as by a turbine, rotates the inducer  10 , typically at a rotational speed of between 0 rpm and 100,000 rpm. As a result, liquid propellant enters the inducer at the inlet  80  at a relatively low pressure, nominally with some positive margin from the propellant vapor pressure, and exits the discharge  90  at a considerably higher pressure, nominally that of a head coefficient ranging from 0.05 to 0.4, where the head coefficient is the inducer pressure rise normalized with the inducer dynamic pressure based on tip speed. 
         [0036]    The partial shroud described herein eliminates tip vortex cavitation and associated vibrations while limiting the length and weight of the shroud to the minimum necessary to accomplish this specific objective without the deleterious effects of a traditional full shroud. The partial shroud may also support the partial blades (reference number  24  in  FIG. 5 ) disclosed below. 
         [0037]      FIG. 4  illustrates alternate blade cavitation in a two-blade inducer as discussed above. A short cavity  60  has formed on one blade and a long cavity  62  has formed on the other blade. The unbalanced blades may lead to adverse radial forces reducing bearing life. In accordance with a second embodiment,  FIGS. 5 and 6  illustrate a pair of short inducer blades  24  offset by 90° from the full size inducer blades  18 . The benefit of a two blade system, lower blade blockage enabling design for a very low inlet flow coefficient, is combined with the benefits of a four blade system, with symmetric and thus balanced alternate blade cavitation. The problem of radial loads due to asymmetric alternate blade cavitation in a two bladed inducer is thus overcome by introducing two short partial blades  24  at the inlet face  14  adjacent the partial shroud  22 . 
         [0038]    It is believed that the two short partial blades  24  provide sites for two short cavities  60  to form allowing the two full size inducer blades  18  to develop two stable, long cavities  62 . As a result, the two bladed inducer  70  with short partial blades functions as a four bladed inducer with respect to alternate blade cavitation, with the associated benefit of low radial load. The partial short inducer blades  24  only span a fraction of the full blade height. The size of the short partial blade  24  is the minimum necessary to provide a site for sheet cavity stabilization and is typically from 5% to 75% of the full blade height and causes a negligible blade blockage compared to an inducer with four full blades. It is further believed that the partial short inducer blades  24  alternating with full size blades  18  will encourage formation of a benign alternate blade cavitation pattern over a wider range of operating conditions than is observed with conventional four bladed inducers, thereby curtailing the range over which an undesirable rotating cavitation exists. This rotating cavitation phenomenon is linked to inlet pressure oscillations and system vibrations, and is particularly prevalent in 3-bladed inducers. 
         [0039]    Partial blades in 3-bladed inducers are expected to convert the undesirable rotating cavitation to the benign alternate blade cavitation resembling that of a 6-bladed inducer, without the excessive blade blockage of the full six blades. 
         [0040]    The short partial blade  24  is supported only at the shroud  22  by a fillet  64  (not visible) and has a length smaller, equal to or greater than its height. The leading edge  66  of this short partial blade  24  can be profiled to match the leading edge  68  of the full size blade  18 , or may be deliberately different in thickness and blade angle. The trailing edge  73  of the short partial blade  24  is profiled to prevent vibrations by using large enough fillets and blade thickness. 
         [0041]    The short partial blades  24  may be cast or machined integral with the shroud or attached, such as by brazing, welding, screwing or riveting. 
         [0042]    Alternatively, as shown in  FIG. 7 , the short partial blades  24  may have an inner end  75  affixed to the inducer hub  12  and an outer end  74  extending toward the tip  16  of a full size blade  18 . The outer end  74  terminates before the radius of the full size blade  18  is reached. 
         [0043]    Furthermore, as shown in  FIG. 8 , two sets of partial blades—one set  24  attached to the hub and the other set  24 ′ attached to the shroud may be used simultaneously, combining the features of the partial blades  24  illustrated in  FIG. 6  and  FIG. 7 . In addition, as shown in  FIG. 9 , either or both sets of partial blades  24  may be off-set axially from the full size blades  18 , preferably in the upstream direction, and one set of partial blades may be off-set circumferentially from the other set. 
         [0044]    The front-end partial shroud in combination with a back flow deflector  23  in  FIG. 1  will extend the operating range of the inducer down to very low inlet flow rates facilitating a wider overall pump operating range. 
         [0045]    One application of the inducer disclosed herein is the Advanced Upper Stage Engine Program (AUSEP). The inducer enables operation of a liquid oxygen turbopump at an inlet net positive suction pressure (NPSP) of below 4 psi. At this value, the engine weight and size are retained within targeted limits. The inducer may also be used in other liquid rocket engines or general pumping applications wherever a very low inlet NPSP or high suction specific speed is required. 
         [0046]    One or more embodiments of the present invention have been described. Nevertheless, it will be understood that various modifications may be made without departing from the spirit and scope of the invention. Accordingly, other embodiments are within the scope of the following claims.