U.S. patent application number 11/484734 was filed with the patent office on 2009-03-19 for radial turbine wheel structure.
This patent application is currently assigned to INDUSTRIAL TECHNOLOGY RESEARCH INSTITUTE. Invention is credited to Shih-Tsao Huang, Chia-Wen Lee, Kuang-Hua Lin, Jia-Ruey Wu.
Application Number | 20090074580 11/484734 |
Document ID | / |
Family ID | 40481701 |
Filed Date | 2009-03-19 |
United States Patent
Application |
20090074580 |
Kind Code |
A1 |
Wu; Jia-Ruey ; et
al. |
March 19, 2009 |
RADIAL TURBINE WHEEL STRUCTURE
Abstract
A radial turbine wheel structure comprises a wheel disc, a
plurality of full blades and a plurality of splitting blades. The
splitting blades are disposed equidistantly around the wheel disc
and are alternately disposed with the full blades. Wherein each of
inlet shrouds, outlet shrouds, inlet hubs and outlet hubs
separately has an included angle to a meridian plane of the wheel
disc, and the full blades are related to the splitting blades in
length. Hence, the radial turbine wheel is applied to the gas
turbine generator set to increase the electricity generation
efficiency of the gas turbine generator.
Inventors: |
Wu; Jia-Ruey; (Jhudong
Township, TW) ; Lin; Kuang-Hua; (Banciao City,
TW) ; Huang; Shih-Tsao; (Taichung City, TW) ;
Lee; Chia-Wen; (Niaosong Township, TW) |
Correspondence
Address: |
RABIN & Berdo, PC
1101 14TH STREET, NW, SUITE 500
WASHINGTON
DC
20005
US
|
Assignee: |
INDUSTRIAL TECHNOLOGY RESEARCH
INSTITUTE
|
Family ID: |
40481701 |
Appl. No.: |
11/484734 |
Filed: |
July 12, 2006 |
Current U.S.
Class: |
416/183 |
Current CPC
Class: |
F01D 5/141 20130101;
F01D 5/34 20130101 |
Class at
Publication: |
416/183 |
International
Class: |
F01D 5/22 20060101
F01D005/22 |
Foreign Application Data
Date |
Code |
Application Number |
Mar 17, 2006 |
TW |
95109324 |
Claims
1. A radial turbine wheel structure, comprising: a wheel disc; a
plurality of full blades equidistantly disposed around the wheel
disc; and a plurality of splitting blades equidistantly disposed
around the wheel disc and alternately disposed with the full
blades; wherein each shroud inlet angle of the full blades is 9.5
to 10.5 degrees, each shroud outlet angle of the full blades is
59.5 to 60.5 degrees, each hub inlet angle of the full blades is 1
to 2 degrees and each hub outlet angle of the full blades is 36.9
to 37.9 degrees; the proportion between each shroud outlet radius
of the splitting blades and each shroud outlet radius of the full
blades is 0.72 to 0.74, the proportion between each hub outlet
radius of the splitting blades and each shroud outlet radius of the
full blades is 0.29 to 0.31, the proportion between each shroud
outlet axial length of the splitting blades and each shroud outlet
axial length of the full blades is 0.66 to 0.68 and the proportion
between each hub outlet axial length of the splitting blades and
each shroud outlet axial length of the full blades is 0.73 to
0.75.
2. The radial turbine wheel structure as in claim 1, wherein the
numbers of the full blades and the splitting blades are both
eight.
3. The radial turbine wheel structure as in claim 1, wherein the
shroud outlet angle is an included angle between an outlet shroud
and a meridian plane of the wheel disc, the shroud inlet angle is
an included angle between an inlet shroud and the meridian plane of
the wheel disc, the hub outlet angle is an included angle between
an outlet hub and the meridian plane of the wheel disc and the hub
inlet angle is an included angle between an inlet hub and the
meridian plane of the wheel disc.
4. The radial turbine wheel structure as in claim 1, wherein the
best proportion between each shroud outlet radius of the splitting
blades and each shroud outlet radius of the full blades is 0.730 to
0.732.
5. The radial turbine wheel structure as in claim 1, wherein the
best proportion between each hub outlet radius of the splitting
blades and each hub outlet radius of the full blades is 0.304 to
0.306.
Description
BACKGROUND OF THE INVENTION
[0001] 1. Field of the Invention
[0002] The present invention relates to a turbine wheel structure,
and more particularly to a radial turbine wheel structure is
applied to a gas turbine generator.
[0003] 2. Description of the Prior Art
[0004] A gas turbine generator conforms to the demands of the high
heat efficiency and the lower air pollution. In addition, the gas
turbine generator has the market competitiveness advantage of less
elements, lower vibration class, lower noise, faster starting,
longer life, smaller volume and lighter weight than the diesel
generator, and without cooling device.
[0005] Although general gas turbine has extremely high burning
efficiency, the simple-cycle small gas turbine set has heat
efficiency about 13% to 17%. For this reason, generally, there are
three ways to improve the heat efficiency of the gas turbine:
[0006] 1. To improve the design of the burner for controlling gas
temperature distribution and use the DLN (dry low NOx) and the
catalyst to restrain the amount of the NOx;
[0007] 2. To use the ceramics material to bear higher temperature
for increasing the inlet temperature of the gas turbine; and
[0008] 3. To install the heat exchanger to increase the heat
efficiency of the gas turbine.
[0009] A gas turbine wheel had been designed by Turbo Tech Company,
but the static adiabatic efficiency parameter gives 82% only. It
needs to be improved. The other prior art of gas turbine wheel of
the U.S. Pat. Nos. 5,213,473, 5,639,217 and 5,730,582 are disclosed
in order to reduce friction loss and fluid resistance force between
the wheels and the air.
SUMMARY OF THE INVENTION
[0010] An object of the present invention is to provide a radial
turbine wheel structure that using CFD design software to model a
set of radial turbine blade forms, and verifying flow field
distribution, friction loss, fluid resistance force and structure
strength by a 3D analysis software to conform the blade contour and
the wheel structure strength to fit in with the operation
environment so as to improve the heat efficiency of the radial
turbine and increase the electricity generation efficiency of the
gas turbine generator.
[0011] For achieving the objective stated above, the present
invention provides a radial turbine wheel structure, comprising a
wheel disc, a plurality of full blades and a plurality of splitting
blades. The splitting blades are disposed equidistantly around the
wheel disc and are alternately disposed with the full blades.
Wherein each shroud inlet angle of the full blades is 9.5 to 10.5
degrees, each shroud outlet angle of the full blades is 59.5 to
60.5 degrees, each hub inlet angle of the full blades is 1 to 2
degrees and each hub outlet angle of the full blades is 36.9 to
37.9 degrees; the proportion between each shroud outlet radius of
the splitting blades and each shroud outlet radius of the full
blades is 0.72 to 0.74, the proportion between each hub outlet
radius of the splitting blades and each shroud outlet radius of the
full blades is 0.29 to 0.31, the proportion between each shroud
outlet axial length of the splitting blades and each shroud outlet
axial length of the full blades is 0.66 to 0.68 and the proportion
between each hub outlet axial length of the splitting blades and
each shroud outlet axial length of the full blades is 0.73 to 0.75.
Hence, the radial turbine wheel provides higher electricity
generation efficiency of the gas turbine generator.
[0012] It is to be understood that both the foregoing general
description and the following detailed description are exemplary,
and are intended to provide further explanation of the invention as
claimed. Other advantages and features of the invention will be
apparent from the following description, drawings and claims.
BRIEF DESCRIPTION OF THE DRAWINGS
[0013] The above and further advantages of this invention may be
better understood by referring to the following description, taken
in conjunction with the accompanying drawings, in which:
[0014] FIG. 1 is a front view of a wheel structure of the present
invention;
[0015] FIG. 2 is a side view of the wheel structure of the present
invention;
[0016] FIG. 3 is a partial enlarged perspective view of the wheel
structure of the present invention;
[0017] FIG. 4 is an angle definition view of the present
invention;
[0018] FIG. 5 is a schematic view of the present invention is
applied to a gas turbine power system; and
[0019] FIG. 6 is a schematic view of the present invention is
applied to a gas turbine generator.
[0020] The drawings will be described further in connection with
the following detailed description of the present invention.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
[0021] Reference is made to FIG. 1 which is a front view of a wheel
structure of the present invention. The present invention provides
a radial turbine wheel 1 comprises a wheel disc 11, a plurality of
full blades 12 and a plurality of splitting blades 13. The numbers
of the full blades 12 and the splitting blades 13 are both eight,
and the full blades 12 are equidistantly disposed around the wheel
disc 11 and the splitting blades 13 are equidistantly disposed
around wheel disc 11 and alternately disposed with the full blades
12.
[0022] Reference is made to FIG. 2 which is a side view of the
wheel structure of the present invention. The blade outlets of the
full blades 12 are truncated to form the splitting blades 13, so
the structure of the splitting blades 13 is identical with the
blade inlets of the full blades 12.
[0023] Reference is made to FIG. 3 which is a partial enlarged
perspective view of the wheel structure of the present invention.
The blade structure of the full blades 12 and the splitting blades
13 are curved structure and rule surfaces, and each of the outlet
shrouds 121, 131, inlet shrouds 122, 132, outlet hubs 123, 133 and
inlet hubs 124, 134 separately has a corresponding equivalent
included angle to a meridian plane (r-z plane is constructed from a
radial plane of the wheel disc and an axial plane of the wheel
disc) of the wheel disc 11.
[0024] The amount of the blades of the radial turbine wheel 1
affects an export force of the turbine, that is the amount of the
blades are larger and the export force is larger. However, the
amount of the blades are larger, the areas between the outlet
blades are smaller; so that is easy to block the airflow so as to
affect the power efficiency and also damage the blades. Hence, the
amount of the blades of the radial turbine wheel 1 are sixteen, and
the splitting blades 13 are truncated so as to increase the areas
between the outlet blades and maintain the export force from
sixteen blades to produce sufficient power efficiency. The main
cause of the export force is the structure of the blades includes
angle distributions of the blades, sizes of the blades and
thickness distributions of the blades; hence, the present invention
provides a blade structure for producing the best export force.
[0025] References are made from FIG. 2 to FIG. 4. A shroud outlet
angle .beta.1 is an included angle between the outlet shroud 121
and a meridian plane of the wheel disc 11, a shroud inlet angle
.beta.2 is an included angle between the inlet shroud 122 and the
meridian plane of the wheel disc 11, a hub outlet angle .beta.3 is
an included angle between the outlet hub 123 and the meridian plane
of the wheel disc 11 and a hub inlet angle .beta.4 is an included
angle between the inlet hub 124 and the meridian plane of the wheel
disc 11. Each of the angles is defined: the shroud outlet angle
.beta.1 and the shroud inlet angle .beta.2 are separately the
included angle between a blade shroud curve C1 that an outer edge
of the full blade 12 is projected in the meridian plane and the
outlet shroud 121, and the included angle between the blade shroud
curve C1 and the inlet shroud 122; the hub outlet angle .beta.3 and
the hub inlet angle .beta.4 are separately the included angle
between a blade hub curve C2 that is the intersection of the
meridian plane and the wheel disc 11, and the outlet hub 123, and
the included angle between the blade hub curve C2 and the inlet hub
124. The full blade 12 is disposed on the wheel disc 11, a shroud
outlet axial length L1 of the full blade 12 is equal to a distance
between the inlet hub 124 of the full blade 12 and the outlet
shroud 121 in axial direction (z-direction); a shroud outlet radius
R1 of the full blade 12 is equal to a distance between the outlet
shroud 121 and an axial line of the wheel disc 11. The splitting
blades 13 are formed by truncating the full blades 12, and
therefore the splitting blades 13 are characterized in the
positions of truncated points. A shroud outlet axial length L2 of
the splitting blade 13 is equal to a distance between the inlet hub
134 of the splitting blade 13 and the outlet shroud 131 in axial
direction; a hub outlet axial length L3 of the splitting blade 13
is equal to a distance between the inlet hub 134 of the splitting
blade 13 and the outlet hub 133 in axial direction. In addition, a
shroud outlet radius R2 of the splitting blade 13 is equal to a
distance between the outlet shroud 131 and the axial line of the
wheel disc 11; a hub outlet radius R3 of the splitting blade 13 is
equal to a distance between the outlet hub 133 and the axial line
of the wheel disc 11.
[0026] The radial turbine wheel structure is characterized in that
wherein each shroud outlet angle .beta.1 of the full blades 12 is
59.5 to 60.5 degrees, each shroud inlet angle .beta.2 of the full
blades 12 is 9.5 to 10.5 degrees, each hub outlet angle .beta.3 of
the full blades 12 is 36.9 to 37.9 degrees and each hub inlet angle
.beta.4 of the full blades 12 is 1 to 2 degrees. The proportion
between each shroud outlet radius R2 of the splitting blades 13 and
each shroud outlet radius R1 of the full blades 12 is 0.72 to 0.74,
the proportion between each hub outlet radius R3 of the splitting
blades 13 and each shroud outlet radius R1 of the full blades 12 is
0.29 to 0.31. In addition, the proportion between each shroud
outlet axial length L2 of the splitting blades 13 and each shroud
outlet axial length L1 of the full blades 12 is 0.66 to 0.68 and
the proportion between each hub outlet axial length L3 of the
splitting blades 13 and each shroud outlet axial length L1 of the
full blades 12 is 0.73 to 0.75. Hence, the characteristics stated
above make the radial turbine wheel 1 with a high export force and
a high output power. Besides, when the proportion between each
shroud outlet radius R2 of the splitting blades 13 and each shroud
outlet radius R1 of the full blades 12 is 0.730 to 0.732 and the
proportion between each hub outlet radius R3 of the splitting
blades 13 and each hub outlet radius R1 of the full blades 12 is
0.304 to 0.306, the radial turbine wheel 1 provides the maximum of
export force and the best output efficiency. The Static Adiabatic
Efficiency parameter of the present invention is 85% that is
calculated and simulated by the representative software of STAR_CD
and ANSYS. Comparing with the gas turbine wheel designed by Turbo
Tech Company, the present invention is better with more than 3% of
static adiabatic efficiency.
[0027] Reference is made to FIG. 5. The radial turbine wheel
structure of the present invention can applied to a gas turbine
system 2. Firstly, a centrifugal compressor 212 of a power system
21 is rotated to draw in the ambient air and transmit the ambient
air to a pot-shaped combustor 213, and a fuel supply device 22
provides fuel to the pot-shaped combustor 213 via a fuel control
valve 221 for burning. And next, the gas produced is transmitted to
a centripetal turbine 211, and the centripetal turbine 211 exhausts
the gas to produce power. The centrifugal compressor 212 and the
centripetal turbine 211 are connected with a drive shaft 214 and
the centripetal turbine 211 outputs the power by the drive shaft
214, and a lubricant supply device 23 provides lubricant to the
drive shaft 214 for lubricating.
[0028] Reference is made to FIG. 6. The radial turbine wheel
structure of the present invention can also applied to a gas
turbine generator. The gas turbine system 2 is connected with a
speed reducer 25 by the drive shaft 214, and the speed reducer 25
is connected with a generator 24 by a coupling 253. Firstly, a
starter 251 of the speed reducer 25 starts gear reducers 252 for
rotating the centrifugal compressor 212 to draw in the ambient air
and transmit the ambient air to the pot-shaped combustor 213. And
next, the fuel supply device 22 provides fuel to the pot-shaped
combustor 213 via the fuel control valve 221 for burning. The gas
produced is exhausted by the centripetal turbine 211 to produce the
power to rotate the gear reducers 252 so as to rotate the coupling
253 to drive the generator 24 to generate the electricity. Due to
the high rotation speed of the centripetal turbine 211, the gear
reducers 252 are used to reduce the speed of the centripetal
turbine 211 to protect the generator 24. In addition, the lubricant
supply device 23 provides the lubricant either to the drive shaft
214 or to the gear reducers 252.
[0029] Although the present invention has been described with
reference to the preferred embodiment thereof, it will be
understood that the invention is not limited to the details
thereof. Various substitutions and modifications have been
suggested in the foregoing description, and others will occur to
those of ordinary skill in the art. Therefore, all such
substitutions and modifications are intended to be embraced within
the scope of the invention as defined in the appended claims.
* * * * *