CN103511008B - Diffuser for turbomachines - Google Patents
Diffuser for turbomachines Download PDFInfo
- Publication number
- CN103511008B CN103511008B CN201310240850.4A CN201310240850A CN103511008B CN 103511008 B CN103511008 B CN 103511008B CN 201310240850 A CN201310240850 A CN 201310240850A CN 103511008 B CN103511008 B CN 103511008B
- Authority
- CN
- China
- Prior art keywords
- diffuser
- wall
- curve
- turbine
- straight
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000011084 recovery Methods 0.000 description 6
- 238000005457 optimization Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000011218 segmentation Effects 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a diffuser for turbomachines. The diffuser is described with an entry section close to the last stage of a turbine having an outer wall including several subsequent straight wall parts at an angle to each other followed by a curved wall part with the curved wall part connecting the straight wall parts to a diffuser lip or exit and having as vertical cross-section a non-circular 2 nd order curve, preferably part of an elliptic curve.
Description
Technical field
The present invention relates to the improvement to the diffuser for turbo machine.It in particular but the diffuser do not related to exclusively after the final stage of low pressure (LP) steamturbine.
Background technique
The diffuser set up in Large steam turbine is for such as guiding to condenser by steam from the final stage of turbine.The wall of the essentially concentric that diffuser so has two or more at least initial rotor axis around turbine with axial orientation and arranges.
As such as U. S. Patent the 6th, 602, described in No. 046, the diffuser after final stage has following task: flowing medium is slowed down, increase across the available pressure drop of turbine or enthalpy drop, a certain proportion of kinetic energy is converted to pressure energy and reduce towards the flow losses of the diffuser outlet of condenser group.Therefore clear, the design of diffuser contributes to the total efficiency of turbo machine, and has made many effort for this reason to optimize the layout of diffuser.
On June 6th to 10,2011 in American Society of Mechanical Engineers (ASME) the turbine fair (Turbo Expo) 2011 that Vancouver city, Columbia Province of Britain, Canada holds time GT2011 in by Ch. Musch, H, the title that Stuer and G. Hermle issues is in the document of " OPTIMIZATION STRATEGY FOR A COUPLED DESIGN OF THE LAST STAGE AND THE SUCCESSIVE DIFFUSER IN A LOW PRESSURE ENVIRONMENT ", author illustrates a kind of diffuser design, its external wall cross-section formed with another straight sections by two angled straight lines and radial direction outlet port of following camber line below.
As described in ' 046 patent, straight line may form a series of kink (kinks) in the wall of diffuser, thus has a mind to cause and wall flow separation.This structure allows the pulsation suppressing shock-induced boundary layer.But this measure can be associated with the very big minimizing of diffuser efficiency.
Consider prior art, the efficiency optimizing the low-voltage module or turbine that thus existing diffuser design also improves the especially steam-powered power equipment of turbo machine further can be regarded as object of the present invention.
Summary of the invention
According to an aspect of the present invention, provide a kind of diffuser with outer wall, outer wall has the entrance part section of close turbine final stage, it comprises some continuous linear portion sections being in a certain angle each other, follow curve part section after it, wherein, curve part section has the vertical cross section as the curve of order 2, this curve of order 2 is preferably oval sections, but except circular segment.
The curve of order 2 than circular can be described according to the algebraic equation of the such as rectangular coordinates of following form:
Wherein, at least one mixing coefficient is not 0.
Having been found that the diffuser lip by using elliptical shape, a kind of better diffuser design may be obtained with regard to aerodynamic force and performance.Especially, on inflow direction, higher curvature may be had in the first portion of curve part section, and towards diffuser exit, there is the curvature of minimizing.Because the top of exhaust stage blade is sprayed, thus also may optimize the subtended angle (or open angle) of diffuser and area ratio and than camber line closer to ideal value, thus the more multi-steering of the flowing in diffuser can be realized in the straight sections of the first angle or kink.
These and other aspect of the present invention becomes clear by from following detailed description and the following accompanying drawing listed.
Accompanying drawing explanation
Now with reference to accompanying drawing, exemplary embodiments of the present invention is described, in the accompanying drawings:
Fig. 1 shows the schematically vertical cross section of the known diffuser with potential Optimal Parameters for low-pressure steam turbine level;
Fig. 2 shows the schematically vertical cross section of the diffuser according to example of the present invention of the known diffuser based on Fig. 1; And
Fig. 3 is the plotted curve of the segmentation diffuser recovery rate, which show the potential efficiency gain surmounting known diffuser according to diffuser of the present invention.
Embodiment
The aspect of example of the present invention and details will be described by the example of the diffuser being used for low-pressure steam turbine in the following description in further detail.
Show the schematically vertical cross section of the diffuser for low-pressure steam turbine level proposed in above mentioned GT2011 publication in FIG.The figure illustrates the cross section of upper half part of substantially rotational symmetric diffuser.It also shows a part for rotor 10 and inner casing 11.Rotation blade and stator vane to lay respectively between rotor and inner casing and are attached to rotor or inner casing.The final stage of turbine comprises the stator vane 111 being circumferentially attached to shell 11 and the rotor blade 101 being circumferentially attached to rotor 10.
Be diffuser 12 after final stage 111,101.It has outer wall 121 and the inwall 122 of the inside radius forming diffuser, this outer wall 121 and inwall 122 form ring duct jointly, thus steam is guided to condenser (not shown), and all extend to diffuser lip 124, it together form diffuser exit 123.The detail drawing that Fig. 1 amplifies shows a part for the outer wall 121 of diffuser, and shows the parameter that can be used for optimizing diffuser for given turbine and vapor stream.Along the direction of vapor stream, wall has the first straight length part l1, follows the second straight length part l2 after it.Second straight section is relative to horizontal line i.e. in axial direction angulation δ 1.Curved portion is followed after these two straight sectioies.Curved portion has angle δ 2 and radius R in its ingress relative to horizontal line, and has angle δ 3 in its outlet port relative to horizontal line.Follow another basic straight sections after camber line, its direction along outlet 123 is with length l3.As described in GT2011 reference, shown all parameters can be changed, with the diffuser 12 of constitution optimization.
Show the diffuser of the amendment of the diffuser based on Fig. 1 (as shown in dotted line 121) according to example of the present invention in fig. 2.This novel diffuser have more big figure straight section (3/4ths) and after straight section the curve 21 of more high-order.Curve 21 is essentially elliptic curve.
As shown in Figure 2, compare with circular curve 121 (shown in dotted line), elliptical shape 21 has higher curvature in beginning or ingress, and towards the more smooth part of the outside stretching one-tenth of outlet 123.When representing same or similar element, other label in Fig. 2 is identical with Fig. 1.
Show the comparison of the efficiency of two kinds of designs of Fig. 2 in figure 3, which show the recovery rate of segmentation diffuser.This figure is the medium velocity C by m/s in units of in axial direction of the recovery rate Chi between diffusor entry (exhaust stage blade outlet) and diffuser exit (2R plane) relative to diffusor entry place
z ωplotted curve.Line more shows the recovery rate of novel diffuser.This recovery rate is at least high by 3% than the known diffuser shown in Fig. 1.Compare according to this, obviously make use of hybrid diffuser of the present invention and there are the potentiality improving the diffuser recovery rate in very big mode.Diffuser than the prior art of Fig. 1 can be regarded as with the better diffuser improving potentiality with 4 or more hybrid diffusers of following oval straight section below.
When by this novel diffuser with when utilizing multiple such as seven or more straight sectioies to omit compared with the design of any curved portion for outer wall simultaneously, similar improvement can be manifested.
With the more straight section of big figure and the diffuser angulation in-between of corresponding length thereof, after follow the curve of following general shape,
Wherein, at least one mixing coefficient is non-vanishing, and this diffuser has the potentiality of higher further improvement than the more limited design following prior art.
Optimization so realizes by using other method described in any known instrument such as ANSYS CFX or above mentioned GT2011 publication.
Describe the present invention by means of only example above, and can amendment be made within the scope of the invention.The present invention also can comprise any independent feature shown in described herein or implicit or accompanying drawing or implicit, or any combination of any feature so, or any feature so or combination, and it extends to its equivalent.Therefore, range of the present invention and scope should not limited by any above-mentioned exemplary embodiments.
Unless explicitly stated, otherwise each feature disclosed in specification (comprising accompanying drawing) can be used to the alternative features of identical, equivalence or similar object substitute.
Unless outside clearly stating herein, in specification, any discussion of prior art does not admit that prior art so is well-known all the time, or defines a part for general knowledge known in the art.
Symbol list
Rotor 10
Inner casing 11
Stator vane 111
Rotor blade 101
Diffuser 12
Straight section length l1
Straight section length l2
Straight section length l3
Angle δ 2, δ 3
The radius R of circular segment
Outlet 123
Antelabium 124
Curve 21
Claims (2)
1. a diffuser (12), it is in the final stage (101 of turbine, 111) after, there is outer wall (121), described outer wall (121) extends to diffuser lip (124), described diffuser lip (124) forms diffuser exit (123), described outer wall (121) comprises some direct wall parts connected continuously, described direct wall part is in a certain angle each other, follow curved wall portion below, wherein, described curved wall portion is positioned between described direct wall part (3) and described diffuser lip (124), and there is the vertical cross section forming Some Second Order Elliptic curve (21).
2. diffuser according to claim 1 (12), is characterized in that, the number of described direct wall part (3) is four or more.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP12172393.6 | 2012-06-18 | ||
| EP12172393.6A EP2677123B2 (en) | 2012-06-18 | 2012-06-18 | Diffuser for turbomachines |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103511008A CN103511008A (en) | 2014-01-15 |
| CN103511008B true CN103511008B (en) | 2015-07-15 |
Family
ID=46318990
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310240850.4A Active CN103511008B (en) | 2012-06-18 | 2013-06-18 | Diffuser for turbomachines |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20130336783A1 (en) |
| EP (1) | EP2677123B2 (en) |
| JP (1) | JP5726236B2 (en) |
| CN (1) | CN103511008B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP7458947B2 (en) * | 2020-09-15 | 2024-04-01 | 三菱重工コンプレッサ株式会社 | Steam turbine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3430769A1 (en) * | 1984-08-17 | 1986-03-06 | Proizvodstvennoe ob"edinenie turbostroenija, Leningradskij metalličeskij zavod, Leningrad | Low pressure cylinder of a steam turbine |
| CN101563526A (en) * | 2006-11-13 | 2009-10-21 | 阿尔斯通技术有限公司 | Diffuser and exhaust system for turbine |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2960306A (en) * | 1956-01-16 | 1960-11-15 | Gen Motors Corp | Turbine |
| GB1050879A (en) * | 1965-01-28 | |||
| US3802187A (en) * | 1972-06-01 | 1974-04-09 | Avco Corp | Exhaust system for rear drive engine |
| US4344737A (en) * | 1978-01-30 | 1982-08-17 | The Garrett Corporation | Crossover duct |
| DE3206626A1 (en) * | 1982-02-24 | 1983-09-01 | Kraftwerk Union AG, 4330 Mülheim | EXHAUST CHANNEL FOR GAS TURBINES |
| GB9415685D0 (en) * | 1994-08-03 | 1994-09-28 | Rolls Royce Plc | A gas turbine engine and a diffuser therefor |
| DE19905994A1 (en) | 1999-02-15 | 2000-08-24 | Peter Kraus | Procedure to prevent shock boundary layer pulsations with annular diffusers in steam turbines entails providing time-controlled blow-in excitation in rear shell region in dead water zone |
| US8475125B2 (en) * | 2010-04-13 | 2013-07-02 | General Electric Company | Shroud vortex remover |
| US8591185B2 (en) * | 2010-11-16 | 2013-11-26 | General Electric Company | Low pressure exhaust gas diffuser for a steam turbine |
-
2012
- 2012-06-18 EP EP12172393.6A patent/EP2677123B2/en active Active
-
2013
- 2013-06-17 US US13/919,332 patent/US20130336783A1/en not_active Abandoned
- 2013-06-18 CN CN201310240850.4A patent/CN103511008B/en active Active
- 2013-06-18 JP JP2013127715A patent/JP5726236B2/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3430769A1 (en) * | 1984-08-17 | 1986-03-06 | Proizvodstvennoe ob"edinenie turbostroenija, Leningradskij metalličeskij zavod, Leningrad | Low pressure cylinder of a steam turbine |
| CN101563526A (en) * | 2006-11-13 | 2009-10-21 | 阿尔斯通技术有限公司 | Diffuser and exhaust system for turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2677123A1 (en) | 2013-12-25 |
| EP2677123B2 (en) | 2018-04-25 |
| CN103511008A (en) | 2014-01-15 |
| JP5726236B2 (en) | 2015-05-27 |
| EP2677123B1 (en) | 2014-10-08 |
| JP2014001735A (en) | 2014-01-09 |
| US20130336783A1 (en) | 2013-12-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6352936B2 (en) | Centrifugal compressor with twisted return channel vanes | |
| CN102042048B (en) | Exhaust gas diffuser | |
| CN102852857B (en) | High-load super transonic axial gas compressor aerodynamic design method | |
| US9033656B2 (en) | Exhaust system for steam turbine | |
| CN107191412B (en) | A Multistage Axial Compressor with Adaptive Air-Blowing of Front and Back Stator | |
| EP3063414B1 (en) | Centrifugal compressor impeller with blades having an s-shaped trailing edge | |
| CN107435656A (en) | Vortex flow spoiler on propeller | |
| CN106662117A (en) | Centrifugal impeller and centrifugal compressor | |
| KR102346583B1 (en) | Discharge region of a turbocharger turbine | |
| CN103511008B (en) | Diffuser for turbomachines | |
| CN109779698A (en) | A kind of turbine structure that single-shaft multi-stage runoff-axis stream combines | |
| CN105298921B (en) | U-shaped mixing diffuser between two-stage centrifugal compressor stage | |
| EP3129657B1 (en) | Improved scroll for a turbomachine, turbomachine comprising said scroll, and method of operation | |
| CN211778224U (en) | Two-section diffuser | |
| CN112283156B (en) | Gas compressor bleed structure and aeroengine | |
| CN108223434B (en) | Model level and design method of light medium high-energy head compressor with flow coefficient of 0.0618 | |
| JP5826706B2 (en) | Steam turbine | |
| JP2017031947A (en) | Low-pressure steam turbine structure | |
| KR101811223B1 (en) | Steam turbine | |
| CN106837860A (en) | Double pressure ratio centrifugal compressors | |
| JP2017172569A (en) | Axial flow compressor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: Baden, Switzerland Patentee after: ALSTOM TECHNOLOGY LTD Address before: Baden, Switzerland Patentee before: Alstom Technology Ltd. |