STATOR FOR SUPERSONIC COMPRESSOR
A stator. The stator may be used in a supersonic compressor that utilizes a rotor to deliver a gas at supersonic conditions to the stator. The stator includes a plurality of aerodynamic ducts that have converging and diverging portions, for deceleration of gas to subsonic conditions and then for expansion of subsonic gas, to change kinetic energy of the gas to static pressure. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when the aerodynamic ducts are designed for high pressure ratios, and structures for boundary layer control.
1 . A stator, comprising:
a diffuser having a longitudinal axis, said diffuser including one or more aerodynamic ducts configured for diffusing a selected gas received therein, said aerodynamic ducts having a leading edge, a converging portion and a diverging portion that with input of said selected gas at supersonic flow conditions generates a plurality of oblique shock waves (S 1 to S x ) and a normal shock wave (S N ) in said aerodynamic duct, said aerodynamic duct having an effective contraction ratio and an inlet relative Mach number for operation associated with a design operating point selected within a design operating envelope for a selected gas, gas quantity, and gas compression ratio, said one or more aerodynamic ducts further comprising
bypass gas passageways or geometrically adjustable portions, or both, operable to adjust the effective contraction ratio of some or all of said aerodynamic ducts, and
boundary layer control structures comprising one or more of (1) outlet bleed ports for boundary layer removal, (2) inlet jets for energizing a boundary layer by gas injection, and (3) one or more vortex generators.
2 . The stator as set forth in claim 1 , wherein said one or more aerodynamic ducts are wrapped about said longitudinal axis.
3 . The stator as set forth in claim 2 , wherein said one or more aerodynamic ducts are helically arranged about said longitudinal axis.
4 . The stator as set forth in claim 3 , wherein said one or more aerodynamic ducts are helically arranged about said longitudinal axis at a helical angle psi (Ψ) in the range of from about forty-five degrees)(45° to about eighty degrees)(80°).
5 . The stator as set forth in claim 4 , wherein said one or more aerodynamic ducts have a centerline, and wherein orthogonal to said centerline, said one or more aerodynamic ducts have a generally parallelogram cross-sectional shape.
6 . The stator as set forth in claim 5 , wherein associated with said cross-sectional shape, said one or more aerodynamic ducts have an average aspect ratio, expressed as width to height, of about two to one (2:1), or more.
7 . The stator as set forth in claim 5 , wherein associated with said cross-sectional shape, said one or more aerodynamic ducts have an average aspect ratio, expressed as width to height, of about three to one (3:1), or more.
8 . The stator as set forth in claim 5 , wherein associated with said cross-sectional shape, said one or more aerodynamic ducts have an average aspect ratio, expressed as width to height, of about four to one (4:1), or more.
9 . The stator as set forth in claim 3 , wherein said one or more aerodynamic ducts are wrapped in a clockwise direction about said longitudinal axis.
10 . The stator as set forth in claim 3 , wherein said one or more aerodynamic ducts are wrapped in a counterclockwise direction about said longitudinal axis.
11 . The stator as set forth in claim 2 , wherein said stator comprises eleven (11), or fewer, leading edges.
12 . The stator as set forth in claim 4 , wherein said stator comprises seven (7), or fewer, leading edges.
13 . The stator as set forth in claim 4 , wherein said stator comprises five (5), or fewer, leading edges.
14 . A stator, comprising:
a diffuser having a longitudinal axis, said diffuser including one or more aerodynamic ducts configured for diffusing a selected gas received therein, said aerodynamic ducts having a leading edge, a converging portion and a diverging portion that with input of said selected gas at supersonic flow conditions generates a plurality of oblique shock waves (S 1 to S x ) in said aerodynamic duct, said aerodynamic duct having an effective contraction ratio and an inlet relative Mach number for operation associated with a design operating point selected within a design operating envelope for a selected gas, gas quantity, and gas compression ratio, said one or more aerodynamic ducts further comprising
bypass gas passageways or geometrically adjustable portions, or both, operable to adjust the effective contraction ratio of some or all of said aerodynamic ducts, and
boundary layer control structures comprising one or more of (1) outlet bleed ports for boundary layer removal, (2) inlet jets for energizing a boundary layer by gas injection, and (3) vortex generators.
15 . The stator as set forth in claim 14 , wherein said one or more aerodynamic ducts comprise bounding walls, and further comprising outlet bleed ports in one or more of said bounding walls.
16 . The stator as set forth in claim 15 , further comprising bleed sub-chambers adjacent said one or more aerodynamic ducts, said bleed sub-chambers in fluid communication with said outlet bleed ports, said bleed sub-chambers configured for passage therethrough of said selected gas removed through said outlet bleed ports.
17 . The stator as set forth in claim 14 , wherein said bypass gas passageways comprise external passageways fluidly connected with said one or more aerodynamic ducts.
18 . The stator as set forth in claim 14 , wherein said bypass gas passageways are fluidly connected with one or more external passageways that return said discharge gas directly or indirectly to said one or more aerodynamic ducts.
19 . The stator as set forth in claim 14 , wherein said bypass gas passageways comprise internal bypass gas passageways, wherein said internal bypass gas passageways are fluidly connected internally within or adjacent said one or more aerodynamic ducts to return said discharged gas directly to said one or more aerodynamic ducts.
20 . The stator as set forth in claim 14 , wherein said geometrically adjustable portions are positionable between an open, startup condition wherein said converging portion allows sufficient flow of said selected gas through said one or more aerodynamic ducts to establish and position a normal shock within said one or more aerodynamic ducts, and a closed, operating condition in which said converging portion is set to a selected operating position.
21 . The stator as set forth in claim 20 , wherein said geometrically adjustable portions further comprise pivotable members and actuators, said pivotable members driven by said actuators, and wherein said geometrically adjustable portions are sized and shaped to change the shape of said converging portion of said one or more of said one or more aerodynamic ducts when said geometrically adjustable portions are moved with said actuators.
22 . The stator as set forth in claim 14 , wherein said vortex generators are located in said converging portion.
23 . The stator as set forth in claim 14 , wherein said vortex generators are located in said diverging portion.
24 . The stator as set forth claim 14 , wherein each of said vortex generators comprise a base with a forward end and a leading edge extending outward to an outward end.
25 . The stator as set forth in claim 14 , wherein a plurality of vortex generators are provided in each of said aerodynamic ducts.
26 . The stator as set forth in claim 14 , wherein one or more of said one or more aerodynamic ducts are helically arranged about said longitudinal axis.
27 . The stator as set forth in claim 14 , wherein said one or more of said aerodynamic ducts are helically arranged at a substantially constant helical angle about said longitudinal axis.
28 . The stator as set forth in claims 14 , wherein each aerodynamic duct of said one or more aerodynamic ducts comprises a leading edge associated therewith.
29 . The stator as set forth in claim 28 , wherein said leading edge comprises a leading edge radius of from about 0.005 inches to about 0.012 inches.
30 . The stator as set forth in claim 28 , wherein said leading edge defines a leading edge wedge angle of between about five (5) degrees and about ten (10) degrees.
31 . The stator as set forth in claim 28 , further comprising a partition wall downstream from said leading edge.
32 . The stator as set forth in claim 28 , wherein said partition wall divides adjacent aerodynamic ducts, and wherein said leading edge comprises an upstream terminus of said partition wall.
33 . The stator as set forth in claim 14 , wherein each of said one or more aerodynamic ducts has a centerline, and wherein orthogonal to said centerline, one or more of said one or more aerodynamic ducts have a generally parallelogram cross-sectional shape.
34 . The stator as set forth in claim 33 , wherein associated with said cross-sectional shape, said one or more aerodynamic ducts have an average aspect ratio, expressed as width to height, of about two to one (2:1), or more.
35 . The stator as set forth in claim 33 , wherein associated with said cross-sectional shape, said one or more of aerodynamic ducts have an average aspect ratio, expressed as width to height, of about three to one (3:1), or more.
36 . The stator as set forth in claim 33 , wherein associated with said cross-sectional shape, said one or more aerodynamic ducts have an average aspect ratio, expressed as width to height, of about four to one (4:1), or more.