Supersonic compressor with structural arrangement to increase pressure energy in a discharge process fluid received from a centrifugal impeller

Patent metadata

Field	Value
Publication number	US-10240613-B2
Application number	US-201414272667-A
Country	US
Kind code	B2
Filing date	May 8, 2014
Priority date	May 14, 2013
Publication date	Mar 26, 2019
Grant date	Mar 26, 2019

Abstract

A supersonic compressor provided may include an axial inlet and a centrifugal impeller fluidly coupled to the axial inlet. The centrifugal impeller may have a periphery and may be configured to impart energy to process fluid received via the axial inlet and discharge the process fluid from the periphery in at least a partially radial direction. The supersonic compressor may further include a static diffuser circumferentially disposed about the periphery of the centrifugal impeller and configured to receive the process fluid from the centrifugal impeller and convert the energy imparted. The static diffuser may include a plurality of diffuser vanes defining diffuser passageways therebetween. A supersonic ramp may be formed at an end of the at least one diffuser vane proximate the periphery of the centrifugal impeller. The supersonic ramp may be configured to generate a shock wave from the process fluid.

First claim

We claim:

1. A supersonic compressor comprising:
an axial inlet defining an inlet passageway configured to receive and flow a process fluid therethrough;
a rotary shaft configured to be driven by a driver;
a centrifugal impeller mounted about the rotary shaft and fluidly coupled to the axial inlet, the centrifugal impeller having a periphery and configured to impart energy to the process fluid received via the axial inlet and discharge the process fluid, as discharged process fluid, from the periphery in at least a partially radial direction; and
a static diffuser circumferentially disposed about the periphery of the centrifugal impeller and configured to receive the discharged process fluid from the centrifugal impeller and convert the energy imparted, the static diffuser having a plurality of curved diffuser vanes, each diffuser vane respectively defining curved, opposing pressure and suction sides, a leading edge proximate the periphery of the centrifugal impeller and conjoining the suction side, such that an adjacent diffuser vanes of the plurality of diffuser vanes defines a diffuser passageway configured to receive and flow therethrough the discharged process fluid with a velocity of at least Mach 1 and thus forming a flow of supersonic process fluid;
each of the diffuser vanes of the plurality of diffuser vanes having a structural arrangement including a supersonic compression ramp formed along its leading edge, the supersonic compression ramp diverging from the suction side and conjoining with the pressure side, a surface of the supersonic compression ramp arranged at the leading edge of the supersonic compression ramp to generate at the leading edge of the supersonic compression ramp in response to contact with the flow of supersonic process fluid an oblique shock wave, which is reflected by the adjacent diffuser vane of the plurality of diffuser vanes to form a reflective shock wave,
a diffuser passageway arrangement downstream of the supersonic compression ramp where an area of the diffuser passageway increases in a direction of the flow of supersonic process fluid flow, and a normal shock wave is formed upstream of a subsonic diffusion zone in the diffuser passageway in response to flow of supersonic process fluid in the diffuser passageway arrangement, the normal shock wave being normal to the flow direction of the process fluid flow, the subsonic diffusion zone disposed between a diffuser passageway inlet and a diffuser passageway outlet, the structural arrangement including the supersonic compression ramp in each of the diffuser vanes of the plurality of diffuser vanes effective to increase the pressure energy of the discharge process fluid, and the diffuser passageway arrangement downstream of the supersonic compression ramp effective to reduce the velocity of the discharge process fluid exiting the static diffuser.

2. The supersonic compressor of claim 1 , wherein the supersonic compressor further comprises a collector fluidly coupled to the diffuser and configured to collect the discharged process fluid flowing through at least one of the diffuser passageways.

3. The supersonic compressor of claim 2 , wherein the collector is a discharge volute configured to be fluidly coupled to a downstream processing component.

4. The supersonic compressor of claim 1 , wherein the axial inlet comprises a plurality of inlet guide vanes extending into the inlet passageway and configured to condition the process fluid flowing therethrough to include one or more predetermined parameters comprising a swirl, a velocity, a mass flow rate, a pressure, and a temperature.

5. The supersonic compressor of claim 4 , wherein at least one of the plurality of inlet guide vanes is adjustable.

6. The supersonic compressor of claim 1 , wherein the centrifugal impeller is configured to provide a compression ratio of at least about 5:1 and is further configured to rotate via the rotary shaft such that the process fluid flowing therethrough has a supersonic velocity at the periphery.

7. The supersonic compressor of claim 1 , wherein the static diffuser is configured to provide a compression ratio of at least about 2:1, and the static diffuser is further configured to discharge the discharged process fluid flowing therethrough at a subsonic velocity.

8. The supersonic compressor of claim 1 , wherein the diffuser passageway inlet is proximal the periphery of the centrifugal impeller and is fluidly coupled to the centrifugal impeller, and wherein the diffuser passageway outlet is disposed radially outward from the diffuser passageway inlet and fluidly coupled to a collector.

9. The supersonic compressor of claim 1 , wherein the centrifugal impeller comprises a hub and a plurality of blades extending therefrom, each of the plurality of blades comprising a blade leading edge and at least one blade leading edge is not coplanar with at least one other blade leading edge.

10. A supersonic compression system comprising:
a driver comprising a drive shaft, the driver configured to provide the drive shaft with rotational energy;
a supersonic compressor operatively coupled to the driver via a rotary shaft integral with or coupled with the drive shaft, the supersonic compressor having:
an axial inlet defining an inlet passageway configured to flow a process fluid therethrough having a first velocity and first pressure energy;
a centrifugal impeller mounted about the rotary shaft and fluidly coupled to the axial inlet, the centrifugal impeller having a periphery and configured to increase the first velocity and first pressure energy of the process fluid received via the axial inlet and discharge the process fluid, as discharged process fluid, from the periphery in at least a partially radial direction having a second velocity and second pressure energy, the second velocity being a supersonic velocity and thus forming a flow of supersonic process fluid;
a static diffuser circumferentially disposed about the periphery of the centrifugal impeller and configured to receive and reduce the second velocity of the discharged process fluid to a third velocity and increase the pressure energy of the second pressure energy to a third pressure energy, the third velocity being a subsonic velocity and the static diffuser having a plurality of curved diffuser vanes, each diffuser vane respectively defining curved, opposing pressure and suction sides, a leading edge proximate the periphery of the centrifugal impeller and conjoining the suction side, such that an adjacent diffuser vanes of the plurality of diffuser vanes defines a diffuser passageway configured to receive and flow therethrough the flow of supersonic process fluid;
each of the diffuser vanes of the plurality of diffuser vanes having an structural arrangement including a supersonic compression ramp formed along its leading edge, the supersonic compression ramp diverging from the suction side and conjoining with the pressure side, a surface of the supersonic compression ramp arranged at the leading edge of the supersonic compression ramp to generate at the leading edge of the supersonic compression ramp in response to contact with the flow of supersonic process fluid an oblique shock wave, which is reflected by the adjacent diffuser vane of the plurality of diffuser vanes to form a reflective shock wave,
a diffuser passageway arrangement downstream of the supersonic compression ramp where an area of the diffuser passageway increases in a direction of the flow of supersonic process fluid flow, and a normal shock wave is formed in the diffuser passageway upstream of a subsonic diffusion zone in the diffuser passageway in response to flow of supersonic process fluid in the diffuser passageway arrangement, the nor

Assignees

• Lardy Pascal
• Sorokes James M
• Kuzdzal Mark J
• Dresser Rand Co

Inventors

• Lardy Pascal
• Sorokes James M
• Kuzdzal Mark J

Classifications

• F04D25/0686

  specially adapted for submerged use · CPC title

• F04D29/422

  Discharge tongues (F04D17/04 takes precedence) · CPC title

• F04D17/10

  for compressing or evacuating · CPC title

• F04D29/462

  especially adapted for elastic fluid pumps · CPC title

• F05D2240/121

  related to the leading edge of a stator vane · CPC title