U.S. patent application number 13/343021 was filed with the patent office on 2013-07-04 for turbine diffuser.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. The applicant listed for this patent is Manjunath B. C, Vignesh Radhakrishnan, Bala M. Singh, Moorthi Subramaniyan. Invention is credited to Manjunath B. C, Vignesh Radhakrishnan, Bala M. Singh, Moorthi Subramaniyan.
Application Number | 20130170969 13/343021 |
Document ID | / |
Family ID | 47664077 |
Filed Date | 2013-07-04 |
United States Patent
Application |
20130170969 |
Kind Code |
A1 |
Subramaniyan; Moorthi ; et
al. |
July 4, 2013 |
Turbine Diffuser
Abstract
The present application provides a diffuser for use with a gas
turbine. The diffuser may include hub, a number of struts extending
from the hub, and a number of airfoils extending from the hub.
Inventors: |
Subramaniyan; Moorthi;
(Bangalore Karnataka, IN) ; Radhakrishnan; Vignesh;
(Bangalore Kornataka, IN) ; Singh; Bala M.;
(Bangalore Karnataka, IN) ; C; Manjunath B.;
(Bangalore Karnataka, IN) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Subramaniyan; Moorthi
Radhakrishnan; Vignesh
Singh; Bala M.
C; Manjunath B. |
Bangalore Karnataka
Bangalore Kornataka
Bangalore Karnataka
Bangalore Karnataka |
|
IN
IN
IN
IN |
|
|
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
47664077 |
Appl. No.: |
13/343021 |
Filed: |
January 4, 2012 |
Current U.S.
Class: |
415/191 |
Current CPC
Class: |
F01D 5/145 20130101;
F01D 5/14 20130101; F05D 2240/126 20130101; F01D 5/146
20130101 |
Class at
Publication: |
415/191 |
International
Class: |
F01D 9/04 20060101
F01D009/04 |
Claims
1. A diffuser for use with a gas turbine, comprising: a hub; a
plurality of struts extending from the hub; and a plurality of
airfoils extending from the hub.
2. The diffuser of claim 1, wherein one of the plurality of
airfoils is positioned between a pair of the plurality of
struts.
3. The diffuser of claim 1, wherein one or more of the plurality of
airfoils comprises a slot therein.
4. The diffuser of claim 1, wherein one or more of the plurality of
airfoils comprises a hunch back airfoil.
5. The diffuser of claim 4, wherein the hunch back air foil
comprises a spoiler thereon.
6. The diffuser of claim 1, wherein one or more of the plurality of
airfoils comprises a vortex generator airfoil.
7. The diffuser of claim 6, wherein the vortex generator airfoil
comprises a sinusoidal configuration.
8. The diffuser of claim 1, wherein one or more of the plurality of
airfoils comprises a fluidic airfoil.
9. The diffuser of claim 8, wherein the fluidic airfoil comprises
one or more ports thereon.
10. The diffuser of claim 1, wherein one or more of the plurality
of airfoils comprises a high lift airfoil.
11. The diffuser of claim 10, wherein the high lift airfoil
comprises one or more airfoil elements.
12. The diffuser of claim 1, wherein one or more of the plurality
of airfoils comprises a cambered airfoil.
13. The diffuser of claim 12, wherein the cambered airfoil
comprises a thickened configuration.
14. The diffuser of claim 1, wherein one or more of the plurality
of airfoils comprises an extended airfoil.
15. The diffuser of claim 14, wherein the extended airfoil
comprises a forward bend.
16. A diffuser for use with a gas turbine, comprising: a hub; a
plurality of struts extending from the hub; a plurality of airfoils
extending from the hub such that one of the plurality of airfoils
is positioned between a pair of the plurality of struts; and a
casing.
17. The diffuser of claim 16, wherein one or more of the plurality
of airfoils comprises a slot therein.
18. The diffuser of claim 16 wherein one or more of the plurality
of airfoils comprises a spoiler thereon.
19. The diffuser of claim 16, wherein one or more of the plurality
of airfoils comprises a sinusoidal configuration.
20. A diffuser for use with a gas turbine, comprising: a hub; a
plurality of struts extending from the hub; and a plurality of
airfoils extending from the hub; the plurality of airfoils
comprising a plurality of configurations.
Description
TECHNICAL FIELD
[0001] The present application and the resultant patent relate
generally to gas turbine engines and more particularly relate to a
turbine diffuser with an airfoil arrangement to reduce swirl and
flow separation during partial load operations and the like.
BACKGROUND OF THE INVENTION
[0002] Gas turbine engines and the like typically include a
diffuser downstream of the last stage of a turbine. Generally
described, the diffuser converts the kinetic energy of the hot flow
gases exiting the last stage into potential energy in the form of
increased static pressure. The diffuser directs the hot flow gases
through a casing of increasing area in the direction of the flow.
The diffuser generally includes a number of struts mounted onto a
hub and enclosed by the casing. Other configurations also may be
known.
[0003] During partial load operations, a bucket exit tangential
flow angle (swirl) may increase and may lead to flow separation on
the struts and the hub of the diffuser. Flow separation and an
increase in swirl may reduce the diffuser static pressure recovery.
Such a reduction may have an impact on overall gas turbine engine
performance and efficiency.
[0004] There is thus a desire for an improved gas turbine engine
diffuser design. Such an improved design preferably may limit flow
separations and swirl so as to improve overall performance and
efficiency.
SUMMARY OF THE INVENTION
[0005] The present application and the resultant patent thus
provide a diffuser for use with a gas turbine. The diffuser may
include hub, a number of struts extending from the hub, and a
number of airfoils extending from the hub.
[0006] The present application and the resultant patent further
provide a diffuser for use with a gas turbine. The diffuser may
include a hub, a number of struts extending from the hub, a number
of airfoils extending from the hub such that one of the airfoils is
positioned between a pair of the struts, and a casing.
[0007] The present application and the resultant patent further
provide a diffuser for use with a gas turbine. The diffuser may
include a hub, a number of struts extending from the hub, and a
number of airfoils extending from the hub. The airfoils may have a
number of configurations.
[0008] These and other features and improvements of the present
application and the resultant patent will become apparent to one of
ordinary skill in the art upon review of the following detailed
description when taken in conjunction with the several drawings and
the appended claims.
BRIEF DESCRIPTION OF THE DRAWINGS
[0009] FIG. 1 is a schematic diagram of a gas turbine engine
showing a compressor, a combustor, a turbine, and a diffuser.
[0010] FIG. 2 is a partial perspective view of a portion of a
diffuser as may be described herein.
[0011] FIG. 3 is a plan view of portions of the diffuser of FIG.
2
[0012] FIG. 4 is a plan view of portions of an alternative
embodiment of a diffuser as may be described herein.
[0013] FIG. 5 is a plan view of portions of an alternative
embodiment of a diffuser as may be described herein.
[0014] FIG. 6 is a plan view of portions of art alternative
embodiment of a diffuser as may be described herein.
[0015] FIG. 7 is a plan view of portions of an alternative
embodiment of a diffuser as may be described herein.
[0016] FIG. 8 is a plan view of portions of an alternative
embodiment of a diffuser as may be described herein.
[0017] FIG. 9 is a plan view of portions of an alternative
embodiment of a diffuser as may be described herein.
DETAILED DESCRIPTION
[0018] Referring now to the drawings, in which like numerals refer
to like elements throughout the several views, FIG. 1 shows a
schematic view of gas turbine engine 10 as may be used herein. The
gas turbine engine 10 may include a compressor 15. The compressor
15 compresses an incoming flow of air 20. The compressor 15
delivers the compressed flow of air 20 to a combustor 25. The
combustor 25 mixes the compressed flow of air 20 with a pressurized
flow of fuel 30 and ignites the mixture to create a flow of
combustion gases 35. Although only a single combustor 25 is shown,
the gas turbine engine 10 may include any number of combustors 25.
The flow of combustion gases 35 is in turn delivered to a turbine
40. The flow of combustion gases 35 drives the turbine 40 so as to
produce mechanical work. The mechanical work produced in the
turbine 40 drives the compressor 15 via a shaft 45 and an external
load 50 such as an electrical generator and the like.
[0019] The gas turbine engine 10 also may include a diffuser 55.
The diffuser 55 may be positioned downstream of the turbine 40. As
described above, the diffuser 55 may include a number of struts 60
mounted on a hub 65 and enclosed within an outer casing 70. The
diffuser 55 turns the flow of combustion gases 35 in an axial
direction. Other configurations and other components may be
used.
[0020] The gas turbine engine 10 may use natural gas, various types
of syngas, and/or other types of fuels. The gas turbine engine 10
may be any one of a number of different gas turbine engines offered
by General Electric Company. The gas turbine engine 10 may have
different configurations and may use other types of components.
Other types of gas turbine engines also may be used herein.
Multiple gas turbine engines, other types of turbines, and other
types of power generation equipment also may be used herein
together.
[0021] FIG. 2 and FIG. 3 show portions of an example of a diffuser
100 as may be described herein. Generally described, the diffuser
100 may include a number of struts 110 positioned on a hub 120. Any
number of struts 110 may be used. The struts 110 and the hub 120
may have any size or shape. The struts 110 may be enclosed within a
casing that expands in diameter along the flow path therethrough.
The casing may be similar to that described above. Other components
and other configurations also may be used herein.
[0022] The diffuser 100 also may have a number of airfoils 130
positioned on the hub 120. In this example, the airfoils 130 may be
positioned adjacent to the struts 110. Specifically, an airfoil 130
may be positioned between each pair of the struts 110. Any number
of the airfoils 130 may be used herein. The angle, length, size,
shape, and configuration of the airfoils 130 may vary. Airfoils 130
of different configurations may be used herein together. A slot 140
may be positioned through a portion of the airfoil 130. The slot
140 serves to direct the flow of combustion gases 35 therethrough.
The slot 140 may have any desired size, shape, or configuration.
Other components and other configurations may be used herein.
[0023] The use of the airfoils 130 thus corrects the creation of
swirl and reduces flow separation about the struts 110 and the hub
120 of the diffuser 100 through the entire partial load operations.
Moreover, the airfoils 130 may be designed to not incur additional
losses during full load ISO and cold day operations. An increase in
airfoil count/solidity reduces airfoil-strut pitch so as to correct
the swirl and the flow separation. The diffuser 100 thus may
provide improved performance so as to improve overall gas turbine
performance and efficiency.
[0024] The airfoil also may include additional features or
mechanisms as shown in for example, FIGS. 4-9. These additional
features also avoid flow separation on the airfoil and improve
performance. FIG. 4 shows a diffuser 150. The diffuser 150 may
include the strut 110 and a "hunch back"-like airfoil 160
positioned adjacent thereto. The hunch back airfoil 160 may have a
spoiler like configuration 165 to direct the flow of combustion
gases 35.
[0025] FIG. 5 shows a further example of a diffuser 170. The
diffuser 170 may include the strut 110 and a vortex generator
airfoil 180 positioned adjacent thereto. The vortex generator
airfoil 180 may have a largely sinusoidal configuration 185 to
direct the flow of combustion gases 35.
[0026] FIG. 6 shows a further example of a diffuser 190. The
diffuser 190 may include the strut 110 and a fluidic airfoil 200
positioned adjacent thereto. The fluidic airfoil 200 may have a
number of fluidic ports 210 to provide suction and/or blowing so as
to direct the flow of combustion gases 35.
[0027] FIG. 7 shows a further example of a diffuser 220. The
diffuser 220 may include the strut 110 and a high lift airfoil 230
positioned adjacent thereto. The high lift airfoil 230 may include
a number of airfoil elements 240 so as to direct the flow of
combustion gases 35.
[0028] FIG. 8 shows a further example of a diffuser 250. The
diffuser 250 may include the strut 110 and a cambered airfoil 260
positioned adjacent thereto. The cambered airfoil 260 may take a
thickened configuration 270 so as to direct the flow of combustion
gases 35.
[0029] FIG. 9 shows a further example of a diffuser 250. The
diffuser 250 may include the strut 110 and an extended airfoil 280
positioned adjacent thereto. The extended airfoil 280 may take a
forward bend 290 so as to direct the flow of combustion gases
35.
[0030] The diffusers described herein thus may elude airfoils 130
of various sizes, shapes, and configurations. The use of the
airfoils 130 with the struts 110 thus controls the flow separation
and swirl during partial load operations so as to improve overall
efficiency. Many other sizes, shapes, and configurations of
diffusers and airfoils may be used herein.
[0031] It should be apparent that the foregoing relates only to
certain embodiments of the present application and the resultant
patent. Numerous changes and modifications may be made herein by
one of ordinary skill in the art without departing from the general
spirit and scope of the invention as defined by the following
claims and the equivalents thereof.
* * * * *