Patent Application
20180328381
Embodiments of the present invention relate to diffuser passages for gas turbine engine centrifugal compressors.
A gas turbine engine centrifugal compressor includes a rotating impeller arranged to accelerate and, thereby, increase the kinetic energy of air flowing therethrough. A diffuser is generally located immediately downstream of and surrounding the impeller. The diffuser operates to decrease the velocity of the air flow leaving the impeller and transform the energy thereof to an increase in static pressure, thus, pressurizing the air.
Diffusers have generally included a plurality of circumferentially spaced passages which converge to an annular space surrounding the impeller. These passages expand in area downstream of the impeller in order to diffuse the flow exiting the impeller. One such diffuser is disclosed in U.S. Pat. No. 4,027,997 issued to A. C. Bryans on Jun. 7, 1977, and assigned to the assignee of this patent. The diffuser passages in this patent assume an initial circular cross section so as to accommodate with minimal losses the relatively high-flow velocities of the air exiting the impeller and, thereafter, gradually merge into a near-rectangular outlet to minimize losses. Each passage gradually merges from a circular cross section at a throat portion near its inlet end, to a near rectangular cross section at its outlet end defined by two flat opposing parallel sides and two flat opposing curved sides which produce a razor sharp trailing edge at the diffuser outlet. This near rectangular shape of the diffuser outlet optimizes the flow distribution to an annular combustion chamber in flow communication with the diffuser outlet.
A diffuser in U.S. Pat. No. 4,576,550 issued to A. C. Bryans on Mar. 18, 1986, and assigned to the assignee of this patent discloses each of the passages includes a throat portion having a quadrilateral cross section, including two substantially parallel linear sidewalls and two substantially arcuate opposing sidewalls, effective for reducing the length of and, thereby, pressure losses from the annular inlet. The linearity and regularity of the diffuser passages enables the diffuser to be manufactured to close tolerances by electric discharge milling an annular plate utilizing a single tool. This assures uniformity and consistency between diffusers. U.S. Pat. No. 4,576,550 is incorporated herein by reference.
We have found that these diffuser designs either reduce trailing edge blockage with greater than optimum area ratios or with large trailing edge blockages that impair performance of downstream components that remove swirl before flow enters the combustor.
Thus, there continues to be a demand for advancements in diffuser design and geometry that improves aerodynamic performance and reduces the overall engine radial envelope.
A diffuser for a centrifugal compressor includes an annular diffuser housing and a plurality of diffuser flow passages extending through the housing and spaced about a circumference of the housing. Each of the passages includes a throat portion and a diffusing section downstream of the throat portion. The diffusing section includes upstream and downstream diffusing portions. Each of the passages further includes a diffusing passage centerline having a centerline linear portion extending downstream through the throat portion and the upstream diffusing portion of each of the diffuser flow passages and a curved portion of the diffusing passage centerline extending downstream from the centerline linear portion through the downstream diffusing portion.
Adjacent ones of the passages may intersect with each other at radially inner inlet portions of the passages and define a quasi-vaneless annular inlet of the diffuser. Each of the passages may include the throat portion downstream of and integral with one of the inlet portions and the centerline linear portion extending downstream through the inlet portion and the throat portion.
Each of the diffuser flow passages may have an equivalent cone angle varying non-linearly downstream along the curved portion of the diffusing passage centerline through the downstream diffusing portion of the diffuser flow passage. The equivalent cone angle may vary curvedly or curvilinearly downstream along the curved portion of the diffusing passage centerline through the downstream diffusing portion of the diffuser flow passage.
The downstream diffusing portion of each of the diffuser flow passages may include axially spaced apart flat forward facing and aft facing or forward and aft sides.
The downstream diffusing portion of each diffuser flow passage may circumferentially flare and curve in a circumferential direction and include compound curved and angled circumferentially spaced apart first and second sides. The first and second sides may flare away from each other. The first and second sides may curve about the linear portion of the diffusing passage centerline and the first and second sides curve in parallel about the curved portion of the diffusing passage centerline.
The diffuser may be incorporated in a high pressure gas generator having a high pressure rotor including, in downstream flow relationship, a high pressure centrifugal compressor, a combustor, and a high pressure turbine drivingly connected to the high pressure centrifugal compressor. The centrifugal compressor includes an annular centrifugal compressor impeller annularly surrounded by the diffuser.
Illustrated in
The exemplary embodiment of the high pressure compressor 14 illustrated herein includes a five stage axial compressor 30 followed by the centrifugal compressor 18 having an annular centrifugal compressor impeller 32. Outlet guide vanes 40 are disposed between the five stage axial compressor 30 and the single stage centrifugal compressor 18. Compressor discharge pressure (CDP) air 76 exits the impeller 32 and passes through a diffuser 42 annularly surrounding the impeller 32 and then through a deswirl cascade 44 into a combustion chamber 45 within the combustor 52. The combustion chamber 45 is surrounded by annular radially outer and inner combustor casings 46, 47. Air 76 is conventionally mixed with fuel provided by a plurality of fuel nozzles 48 and ignited and combusted in an annular combustion zone 50 bounded by annular radially outer and inner combustion liners 72, 73.
The combustion produces hot combustion gases 54 which flow through the high pressure turbine 16 causing rotation of the high pressure rotor 12 and continue downstream for further work extraction in a low pressure turbine 78 and final exhaust as is conventionally known. In the exemplary embodiment depicted herein, the high pressure turbine 16 includes, in downstream serial flow relationship, first and second high pressure turbine stages 55, 56 having first and second stage disks 60, 62. A high pressure shaft 64 of the high pressure rotor 12 connects the high pressure turbine 16 in rotational driving engagement to the impeller 32. A first stage nozzle 66 is directly upstream of the first high pressure turbine stage 55 and a second stage nozzle 68 is directly upstream of the second high pressure turbine stage.
Referring to
Referring to
Referring to
Referring to
Each passage 22 further includes a diffusing passage centerline 108 equidistantly disposed between the forward and aft walls 101, 100 and adjacent ones of the diffuser vanes 23 in planes 103 normal to the diffusing passage centerline 108. The diffusing passage centerline 108 includes a centerline linear portion 120 extending downstream through the inlet portion 24, the throat portion 28, and the upstream diffusing portion 102 of each of the diffuser flow passages 22. A curved portion 122 of the diffusing passage centerline 108 extends downstream from the centerline linear portion 120 through the curved downstream diffusing portion 104 of each of the diffuser flow passages 22.
The curved portion 122 of the diffusing passage centerline 108 is flat and defines a flat plane 123 normal to the engine axis 25. The inlet portion 24, the throat portion 28, and the upstream diffusing portion 102 of each of the diffuser flow passages 22 are straight. The downstream diffusing portion 104 of each diffuser flow passage 22 is both circumferentially flared and curved in a circumferential direction C. The downstream diffusing portion 104 includes compound curved and angled circumferentially spaced apart first and second sides 116, 117. The first and second sides 116, 117 are flared away from each other and in an embodiment may be linearly flared away from each other in a generally circumferential direction C.
The first and second sides 116, 117 are also curved circumferentially in the same circumferential direction C and amount of degrees (variable angle VA) from the centerline linear portion 120 as is the curved portion 122 of the diffusing passage centerline 108 and, thus, parallel to the curved portion 122. The first and second sides 116, 117 are curved about the linear portion 120 of the diffusing passage centerline 108. In an embodiment, the first and second sides 116, 117 may be circular and, thus, circumscribed about the centerline about the linear portion 120. The circular character of the first and second sides 116, 117 can be seen by circumferentially spaced apart circular first and second edges of a cross-sectional area A normal to the diffusing passage centerline 108 as illustrated in
Referring to
The equivalent cone angle for the curved portion 120 of the diffuser flow passage 22 disclosed herein varies non-linearly and is illustrated as varying curvedly or curvilinearly along the diffusing passage centerline 108. The equivalent cone angle for the curved downstream diffusing portion 104 of the diffuser flow passage 22 disclosed herein may vary curvilinearly as illustrated in
Equivalent Cone Angle can be calculated as follows:
Dh=sqrt(4*A/2/pi) wherein Dh is Hydraulic Diameter and A is the cross-sectional area of the diffuser flow passage 22 (as illustrated in
dDh=change in hydraulic diameter from one portion of the diffuser flow passage 22 to the next.
dL=change in length L along the diffusing passage centerline 108 from one portion of the diffuser flow passage 22 to the next (as illustrated in
Equivalent Cone Angle=arctan(dDh/dL)
While there have been described herein what are considered to be preferred and exemplary embodiments of the present invention, other modifications of the invention shall be apparent to those skilled in the art from the teachings herein and, it is therefore, desired to be secured in the appended claims all such modifications as fall within the true spirit and scope of the invention. Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims.
Embodiments of the present invention were made with government support under government contract No. W911W6-11-2-0009 by the Department of Defense. The government has certain rights to embodiments of the present invention.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/US2014/061020 | 1/9/2015 | WO | 00 |
