NZ215824A

NZ215824A - One-piece, cast diffuser housing for turbine engine

Info

Publication number: NZ215824A
Application number: NZ215824A
Authority: NZ
Inventors: R W Chevis; R G Keetley
Original assignee: Teledyne Ind
Priority date: 1985-04-29
Filing date: 1986-04-14
Publication date: 1987-09-30
Also published as: GB2176539B; SE8601577L; AU5601686A; IT1188109B; FR2581135A1; GB2176539A; GB8610316D0; BR8602136A; SE8601577D0; IT8667345A0; DE3612412A1; IT8667345A1

Description

mmw V./[ ■ - • 215824 Priority Date(s): Complete Specification Filed: Class: Ac) .2 c ^/c?0 Publication Date: P.O. Journal, No: 3 0 S E P 19871 /3°P N.Z. PATENT OFFICE ? " "FP |?S6 •.cceivro PATENTS FORM NO: 5 PATENTS ACT 1953 COMPLETE SPECIFICATION "CENTRIFUGAL COMPRESSOR SYSTEM AND METHOD OF MAKING SAME'1 WE, TELEDYNE INDUSTRIES, INC a corporation of the state of California, U.S.A. of 1901 Avenue of the Stars, Los Angeles, California 90067, U.S.A. hereby declare the invention, for which we pray that a patent may be granted to us, and the method by which it is to be performed, to be particularly described in and by the following statement:- '■ ■ '-/ i'V HX PATENT OFRCI ? 1 r p ' . ' ^ c. • 23 JUL1987 * Background of the Invention flECBVED I. Field of the Present Invention The present invention relates generally to turbine engine constructions, and more particularly, to the structure of a diffuser system disposed downstream of a centrigual compressor in a turbine engine.

II Description of the Prior Art In a turbine engine having a centrifugal compressor, fluid is discharged under pressure radially outwardly from the rotating shaft of the turbine. The turbine engine housing includes passages which direct the fluid toward a combustor chamber formed in the housing. In order to obtain controlled flow characteristics in the discharged fluid so that the fluid mixes and ignites efficiently and completely in the combustor chamber, a diffuser system is often employed in the passage between the centrifugal compressor and the combustor chamber.

Typically the diffuser comprises a pair of annular, radially aligned walls defining a fluid flow passage therebetween sized to provide the desired flow characteristics. In addition, vanes may extend across the passageway between the radially aligned surfaces to further control the direction and velocity and flow envelope of the fluid flow from the diffuser. However, the flow pattern created by the diffuser can be modified or destroyed if the passageway changes direction. Thus, unless the combustor chamber is located radially outwardly from the diffuser passageway, the turbine engine will not perform as efficiently as intended by incorporating the radial diffuser.

Accordingly, in the design of a turbine engine which is to be K enclosed in a narrow turbine housing, it would be advantageous '-V O - - •' ; ' • ° ^ <L. to place the combustor chamber axially downstream from the centrifugal compressor to provide a turbine engine with a minimum breadth. In such a case, it will be understood that the fluid discharged by the compressor must be axially displaced toward the combustor chamber. During this transfer to the combustor chamber, it would be advantageous to provide additional j means for controlling and directing the flow of fluid into the combustor chamber so that the fluid is well dispersed in the combustor chamber. Previously, such control is provided by swirl plate constructions incorporated in the walls of the combustor housing. In such a device, the combustor chamber must be specially constructed and thus adds to the cost and complexity of the turbine engine construction. On the other hand, the housing walls defining the flow passages could also be specially constructed to include diffuser means which would also substantially increase the cost and complexity of the turbine engine.

Summary of the Present Invention The present invention provides a diffuser structure for a turbine engine which has a turbine casing, a turbine shaft disposed in said casing, a centrifugal compressor secured to y said shaft, and a combustor chamber contained in said casing; said diffuser structure fluidly connecting said compressor t-5 and said combustor chamber, and comprising: an annular hub i''1 , -1 ^ • receiving said shaft therein; a flange portion extending to Ittil radially from said hub possessing an annular radially aligned O* \ \ 1 • surface and an annular axially aligned surface, each of said surfaces facing an adjacent portion of said turbine casing; a plurality of first diffuser vanes disposed on said radially aligned surface extending to said turbine casing; a plurality of second diffuser vanes disposed on said axially aligned surface extending to said turbine casing; wherein said hub, said flange, and said first and second plurality of vanes are composed of a continuous material.

The one piece cast housing generally comprises an annular > hub portion whose inner bore is defined by appropriate surfaces such as lands for engagement with bearings which support the turbine shaft. The outer surface of the hub includes appropriate means or orifices for the connection of cooling or lubricating conduits which enable the mechanisms disposed in the interior of the hub to be properly cooled and lubricated. The outermost edges of the diffuser vanes abut against portions of the turbine housing walls to thereby define the fluid passageway intermediate the cast housing and the turbine housing walls with means for controlling the flow of fluid being delivered from the centrigual compressor to ~— i ! - -i—- ri |1,1" 'H ''in i 11 "Trin - 215824 the combustor chamber of the turbine engine.

Thus, the present invention provides a compressor diffuser system with a radial diffuser construction which also incorporates means for forming an axial passage toward a combustor which is axially spaced from a centrifugal compressor. It is, therefore, especially convenient for use in small turbine engines. In addition, since the diffuser vanes are formed together with the surfaces which form fluid passages in the housing, complex and time consuming installation of separately formed and machined diffuser vanes is avoided. In addition, since the cast housing includes axial diffuser vanes, an appropriate swirl or anti-swirl component can be introduced to the fluid flow into the combustor chamber without the need for complete construction of the combustor chamber walls of the turbine housing.

Brief Description of the Drawing The present invention will be more clearly understood by reference to the following detailed description of the preferred embodiment of the present invention, when read in conjunction with the accompanying drawing in which like reference characters refer to like parts throughout the several views, and in which:' Fiff. 1 is a front elevational view of a radial diffuser casting according to the present invention; Fig. 2 is a sectional elevation taken substantially along the line 2-2 of Fig. 1 and including environmental portions of the turbine engine; and Fig. 3 is a top plan view of a portion of the device taken substantially from the view line 3-3 in Fig. 1.

Detailed Description of the Preferred Embodiment of the present invention Referring first to Fig. 2, a turbine engine 12 includes a 215824 centrifugal compressor 14 having compressor blades 16 secured for rotation to the turbine shaft 18. The compressor 14 is confined within the intake structure 19 having a curved portion 20 conforming with the curved configuration of the tips of the blades 16 and which includes a radially aligned, planar surface portion 22 extending radially outwardly from the tips of the final stage of the compressor blades 16. The turbine casing 15 also includes an axially extending wall portion 24 at the outermost end of wall portion 22 which extends rearwardly toward the combustor chamber 26 defined by appropriate housing walls 28. While the turbine engine 12 includes a centrifugal compressor 14 to obtain the advantage of imparting centrifugal force to the fluid in a turbine engine, the combustor chamber 26 is spaced axially away from the centrifugal compressor 14 so that the turbine casing 15 is narrow and provides a compact turbine engine construction. The centrifugal compressor 14 fluidly communicates with the compressor chamber through passages formed by cast housing 30.

Cast housing 30 comprises a one-piece cast housing in which all of the important features are cast integrally therewith and thereafter machined to -appropriate finished surface tolerances. The cast housing 30 comprises an annular hub portion 32 and a radial flange 34 extending radially outwardly from the hub. The peripheral wall defining the bore in the hub 32 is provided with appropriate lands, such as land surface 36, for bearing constructions which support the hub about the rotating turbine shaft 18. In addition, the hub also includes appropriate passages such as passages 38 and 40 which permit lubricant or coolant to be introduced to the bearing structures contained * - 6 - ■i:'-. , ' ' ' v ' ":'sv ft •?15a^4 V-* within the hub 32, as well as appropriate outlet passages such as the passage 42. In any event, it will be seen that the cast housing 30 is secured in the turbine engine 12 by installation on the intake support structure 19 as will be described in detail hereinafter.

P- L. B. A A. cas* housing Of The radial flange 34 of the^diffuser member 30 includes a cone per-x^£, t 2Z! i /g-^portion 44 extending radially outwardly from the periphery of hub 32 which angles outwardly towards a position axially spaced from the hub 32. A radially aligned wall portion 46 of flange — 34 extends outwardly from the outermost end of the web and includes a planar, substantially annular wall surface 48 facing forwardly of the hub 32. The radial wall portion 46 is joined at its outermost end to an axially extending cylindrical wall portion 50 having an outer surface portion 52 extending axially toward the hub and facing radially outwardly from the hub.

As best shown in Fig. 2, surface portion 48 extends radially outwardly above the outlet of the last compressor stage blade 16, and together with intake structure wall 22 defines a radial diffuser passage 56 therebetween. The axially extending surface portion 52 extends from the radial diffuser passage 56 toward the combustor chamber 26 and in conjunction with the turbine casing wall surface 24 defines the passageway 58 therebetween in fluid communication with the combustor chamber 26. A plurality of diffuser vanes 60 are integrally formed on the annular surface 48. As best shown in Fig. 1 the diffuser vanes are cast in an air foil shape which controls the flow i. £5 ! I characteristics of the fluid discharged from the outlet of |$ej f centrifugal compressor 14. Since the diffuser vanes 60 are ** integrally formed with and extend from the surface 48, th 215824 construction eliminates the need for sealing or otherwise interlocking the diffuser means to that side wall of the radial diffuser pasage 56. Of course, various other shapes of vanes are also within the scope of the present invention.

A plurality of diffuser vanes 62 are integrally formed on the axially extending surface 52 and extend radially outwardly from the surface. As best shown in Fig. 3, the diffuser vanes 62 are cast as curved wall portions which reduce the swirl component from the radial diffuser vanes, thereby straightening the flow of fluid introduced to the combustor chamber 26. Of course, various other shapes for the vanes can also be employed. The outer end surfaces of the vanes 60 and 62 abut against and seal with the adjacent intake structure and turbine casing surfaces 22 and 24, respectively, so that the diffuser passages 56 and 58 form a closed passageway between the outlet of the centrifugal compressor 14 and the combustor chamber 26. Appropriate means are also provided for locking the member 30 in its position within the turbine engine. For example, a plurality of axial throughbores 61 are formed in the vanes 60. Bolts can then be inserted through the throughbores 61 and fastened to the intake structure 19 to secure the cast housing 30 in the turbine engine. Of course, surfaces of the diffuser vanes 60, 62 as well as the surfaces 48 and 52 are finished to proper tolerances by machining the surfaces after the entire member 30 has been cast.

Having thus described the important structural features of the present invention, the operation of the device is easily described. Once the centrifugal compressor has been installed on a turbine shaft and the bearings are secured in the hub 32, I 215324 the cast and machined -eaot- housing 30 is positioned over the turbine shaft and slid into position so that radially aligned annular surface 48 is spaced apart a predetermined distance from the intake structure wall surface 22 so as to define the radial diffuser passage 56 therebetween communicating with the outlet of the last stage compressor blade 16. At the same time, the axially extending surface 52 will be spaced apart a predetermined distance from the turbine casing wall surface 24 and defines a fluid passage communicating between a radial diffuser passage 56 and combustor chamber 26. In the preferred embodiment, the width of the diffuser vanes 60 and 62 provide the predetermined spacing between the wall surfaces. It will be understood that securing of the cast housing 30 to the intake structure housing provides a sturdy support for the turbine shaft in the hub 32.

^ The hub 32 can also be bolted to turbine casing structure P? L. B. & A* through the apertured flanges 66 {see i-J. ptr j22/? J5?Thus , the present invention provides a lightweight diffuser system including means for axially transferring fluid from the compressor to the combustor of a small turbine engine in which the combustor is located in a position axially spaced from the centrifugal compressor. Since the cast housing 30 is made in one piece, it is substantially less complex to install than previously known two stage diffusers. In addition, since diffuser vanes are formed on one of the peripheral surfaces of the diffuser passageways, separate production and complex installation of individual vanes is avoided. Nevertheless,, it will be understood that the diffuser vanes can be machined to an appropriate shape within appropriate tolerances. In addition, the. ... cast housing 30 provides additional support for the turbij ^ 215*24 shaft within the turbine engine and, thus, serves to reduce the weight of supporting structure for the turbine shaft within the turbine housing.

Having thus described the invention, many modifications thereto will become apparent to those skilled in the art to which it pertains without departing from the scope of the present invention as defined in the appended claims. 215824

Claims

WHAT WE CLAIM IS:

1. A diffuser structure for a turbine engine which has a turbine casing, a turbine shaft disposed in said casing, a centrigual compressor secured to said shaft, and a combustor chamber contained in said casing; said diffuser structure fluidly connecting said compressor and said combustor chamber, and^ comprising: an annular hub receiving said shaft therein; a flange portion extending radially from said hub possessing an annular radially aligned surface and an annular axially aligned surface, each of said surfaces facing an adjacent portion of said turbine casing; a plurality of first diffuser vanes disposed on said radially aligned surface extending to said turbine casing; a plurality of second diffuser vanes disposed on said axially aligned surface extending to said turbine casing; wherein said hub, said flange, and said first and second plurality of vanes are composed of a continuous material.

2. A diffuser as defined in claim 1 wherein said radially aligned surface is axially spaced from an end of said annular hub and said flange portion includes a cone extending between the innermost end of said radially aligned surface and said hub.

3. A diffuser as defined in claim 1 wherein each of said first diffuser vanes is profiled as an airfoil.

4. A diffuser as defined in claim 1 wherein each of said second diffuser vanes is profiled as a curved wall. 11 215824

5. A diffuser as defined in claim 1 wherein said turbine casing includes an intake structure and said diffuser structure further comprises means for securing said diffuser structure to said intake structure.

6. A diffuser according to claim 5, wherein said securing means comprises an axially aligned throughbore in at least some of said first diffuser vanes and a fastener connected to said intake portion disposed in each through-bore.

7. A diffuser according to claim 1, wherein said continuous material is a material having a cast structure.

8. A diffuser system for use in a turbine engine, substantially as hereinbefore described with reference to and as shown in the accompanying drawings. TELEDYNE INDUSTRIES, INC by their authorized agents P.L. BERRY & ASSOCIATES per: