U.S. patent number 10,385,774 [Application Number 15/268,713] was granted by the patent office on 2019-08-20 for split compressor turbine engine.
This patent grant is currently assigned to United Technologies Corporation. The grantee listed for this patent is United Technologies Corporation. Invention is credited to Tania Bhatia Kashyap, Daniel Bernard Kupratis, Brian Merry, Kevin L. Rugg, Thomas N. Slavens, Gabriel L. Suciu, Arthur W. Utay, Mark F. Zelesky.
United States Patent |
10,385,774 |
Kupratis , et al. |
August 20, 2019 |
Split compressor turbine engine
Abstract
A turbine engine includes a first compressor and a second
compressor fluidly parallel to the first compressor. A reverse flow
combustor is fluidly connected to the first compressor and the
second compressor. A first turbine and a second turbine are fluidly
connected in series, and fluidly connected to an output of the
reverse flow combustor.
Inventors: |
Kupratis; Daniel Bernard
(Wallinford, CT), Kashyap; Tania Bhatia (West Hartford,
CT), Zelesky; Mark F. (Bolton, CT), Utay; Arthur W.
(South Windsor, CT), Suciu; Gabriel L. (Glastonbury, CT),
Slavens; Thomas N. (Moodus, CT), Rugg; Kevin L.
(Fairfield, CT), Merry; Brian (Andover, CT) |
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Farmington |
CT |
US |
|
|
Assignee: |
United Technologies Corporation
(Farmington, CT)
|
Family
ID: |
60019671 |
Appl.
No.: |
15/268,713 |
Filed: |
September 19, 2016 |
Prior Publication Data
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Document
Identifier |
Publication Date |
|
US 20180080373 A1 |
Mar 22, 2018 |
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F02C
3/145 (20130101); F02C 7/04 (20130101); F02C
3/107 (20130101); F05D 2250/30 (20130101); F05D
2240/40 (20130101) |
Current International
Class: |
F02C
3/107 (20060101); F02C 3/14 (20060101); F02C
7/04 (20060101) |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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1626033 |
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Aug 1970 |
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DE |
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2551485 |
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Jan 2013 |
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EP |
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Other References
European Search Report for Application No. 17191922.8 dated Feb.
13, 2018. cited by applicant.
|
Primary Examiner: Bogue; Jesse S
Attorney, Agent or Firm: Carlson, Gaskey & Olds,
P.C.
Claims
The invention claimed is:
1. A turbine engine comprising: a first compressor and a second
compressor in fluid parallel with the first compressor, each of the
first compressor and the second compressor including multiple
compressor stages; a reverse flow combustor fluidly connected to
said first compressor and said second compressor; and a first
turbine and a second turbine in fluid series, and fluidly connected
to an output of the reverse flow combustor.
2. The turbine engine of claim 1, wherein a fluid inlet of the
first compressor and a fluid inlet of the second compressor are
equal sized, such that fluid flow into each of the first compressor
and the second compressor is equal.
3. The turbine engine of claim 1, wherein at least one of said
first turbine and said second turbine is a single stage
turbine.
4. The turbine engine of claim 3, wherein each of said first
turbine and said second turbine is a single stage turbine.
5. The turbine engine of claim 1, wherein said first compressor and
said first turbine are connected to a first spool, and wherein said
second compressor and said second turbine are connected to a second
spool.
6. The turbine engine of claim 5, wherein said first spool and said
second spool are collinear.
7. The turbine engine of claim 1, wherein said first compressor,
said second compressor, said first turbine and said second turbine
are connected to a single spool.
8. The turbine engine of claim 1, wherein at least one of said
first compressor and said second compressor is a direct drive
compressor.
9. The turbine engine of claim 1, wherein said first compressor and
said second compressor are counter-rotating compressors, relative
to each other.
10. The turbine engine of claim 1, wherein said first compressor
and said second compressor are co-rotating.
11. The turbine engine of claim 1, wherein at least one of said
first compressor and said second compressor is comprised of
multiple rotors, each of said rotors being constructed of a
lightweight high strength ceramic.
12. The turbine engine of claim 11, wherein the lightweight high
strength ceramic is a silicon based structural ceramic
material.
13. The turbine engine of claim 12, wherein the lightweight high
strength ceramic comprises one of silicon nitride, silicon carbide,
silicon carbide fiber reinforced ceramic composite, and carbon
fiber reinforced silicon carbide composite.
14. A method for driving a turbine engine comprising: splitting an
inlet flow between a first compressor and a second compressor such
that the second compressor is in fluid parallel with the first
compressor, each of the first compressor and the second compressor
including multiple compressor stages; providing an output flow of
each of said first compressor and said second compressor to a
reverse flow combustor; and driving a first turbine and a second
turbine to rotate by expanding combustion products generated in
said reverse flow combustor across the first turbine and the second
turbine.
15. The method of claim 14, wherein splitting an inlet flow between
the first compressor and the second compressor, comprises splitting
the inlet flow evenly.
16. The method of claim 14, wherein expanding the combustion
products across the first turbine and the second turbine comprises
expanding an output of the first turbine across the second
turbine.
17. The method of claim 14, further comprising driving rotation of
the first compressor via a shaft connecting the first compressor to
the first turbine, and driving rotation of the second compressor
via a shaft connecting the second compressor to the second
turbine.
18. The method of claim 14, further comprising driving rotation of
the first compressor and the second compressor via a shaft
connecting the first compressor and the second compressor to the
first turbine and the second turbine.
19. A turbine engine comprising: a first compressor and a second
compressor in fluid parallel with the first compressor, each of the
first compressor and the second compressor including multiple
compressor stages; a combustor fluidly connected to said first
compressor and said second compressor; and a turbine section
comprising a first turbine and a second turbine downstream of the
first turbine, the turbine section being fluidly connected to an
output of the combustor.
20. The turbine engine of claim 19, wherein each of said first
turbine and said second turbine are single stage turbines.
21. The turbine engine of claim 1, wherein the first turbine and
the second turbine are sized such that the first compressor and the
second compressor are driven to rotate at the same speed.
Description
TECHNICAL FIELD
The present disclosure relates generally to turbine engines, and
more specifically to a split compressor turbine engine.
BACKGROUND
Turbine engines generally compress air in a compressor section, and
provide the compressed air to a combustor. The compressed air is
mixed with a fuel, and ignited within the combustor. The resultant
combustion products are passed to a turbine section, and are
expanded across the turbine section. The expansion of the
combustion products drives rotation of the turbine section. The
turbine section is connected to the compressor section via one or
more shafts, and the rotation of the turbine section, in turn,
drives rotation of the compressor section.
In a typical example, the compressor section and the turbine
section each include multiple compressors and turbines,
respectively. The first compressor, referred to as a low pressure
compressor, compresses ambient air, and provides the compressed air
to the second compressor, referred to as the high pressure
compressor. This arrangement is referred to as the compressors
being in series, and provides compressed air to the combustor
section from a single output source in the compressor section.
SUMMARY OF THE INVENTION
In one exemplary embodiment a turbine engine includes a first
compressor and a second compressor fluidly parallel to the first
compressor, a reverse flow combustor fluidly connected to the first
compressor and the second compressor, and a first turbine and a
second turbine fluidly in series, and fluidly connected to an
output of the reverse flow combustor.
In another example of the above described turbine engine a fluid
inlet of the first compressor and a fluid inlet of the second
compressor are approximately equal sized, such that fluid flow into
each of the first compressor and the second compressor is
approximately equal.
In another example of any of the above described turbine engines at
least one of the first turbine and the second turbine is a single
stage turbine.
In another example of any of the above described turbine engines
each of the first turbine and the second turbine is a single stage
turbine.
In another example of any of the above described turbine engines
the first compressor and the first turbine are connected to a first
spool, and wherein the second compressor and the second turbine are
connected to a second spool.
In another example of any of the above described turbine engines
the first spool and the second spool are collinear.
In another example of any of the above described turbine engines
the first compressor, the second compressor, the first turbine and
the second turbine are connected to a single spool.
In another example of any of the above described turbine engines at
least one of the first compressor and the second compressor is a
direct drive compressor.
In another example of any of the above described turbine engines
the first compressor and the second compressor are counter-rotating
compressors.
In another example of any of the above described turbine engines
the first compressor and the second compressor are co-rotating.
In another example of any of the above described turbine engines at
least one of the first compressor and the second compressor is
comprised of multiple rotors, each of the rotors being constructed
of a lightweight high strength ceramic.
In another example of any of the above described turbine engines
the lightweight high strength ceramic is a silicon based structural
ceramic material.
In another example of any of the above described turbine engines
the lightweight high strength ceramic comprises one of silicon
nitride, silicon carbide, silicon carbide fiber reinforced ceramic
composite, and carbon fiber reinforced silicon carbide
composite.
An exemplary method for driving a turbine engine includes splitting
an inlet flow between a first compressor and a second compressor,
providing an output flow of each of the first compressor and the
second compressor to a reverse flow combustor, and driving a first
turbine and a second turbine to rotate by expanding combustion
products generated in the reverse flow combustor across the first
turbine and the second turbine.
In another example of the above described method for driving a
turbine engine splitting an inlet flow between the first compressor
and the second compressor, comprises splitting the inlet flow
approximately evenly.
In another example of any of the above described methods for
driving a turbine engine expanding the combustion products across
the first turbine and the second turbine comprises expanding an
output of the first turbine across the second turbine.
Another example of any of the above described methods for driving a
turbine engine further includes driving rotation of the first
compressor via a shaft connecting the first compressor to the first
turbine, and driving rotation of the second compressor via a shaft
connecting the second compressor to the second turbine.
Another example of any of the above described methods for driving a
turbine engine further includes driving rotation of the first
compressor and the second compressor via a shaft connecting the
first compressor and the second compressor to the first turbine and
the second turbine.
In one exemplary embodiment a turbine engine includes a first
compressor and a second compressor fluidly parallel to the first
compressor, a combustor fluidly connected to the first compressor
and the second compressor, and a turbine section comprising a first
turbine and a second turbine downstream of the first turbine, the
turbine section being fluidly connected to an output of the
combustor.
In another example of the above described turbine engine each of
the first turbine and the second turbine are single stage
turbines.
These and other features of the present invention can be best
understood from the following specification and drawings, the
following of which is a brief description.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 schematically illustrates a split compressor turbine engine
architecture according to a first example.
FIG. 2 schematically illustrates a split compressor turbine engine
architecture according to a second example.
FIG. 3 illustrates a method for operating a gas turbine engine
according to either of the examples of FIGS. 1 and 2.
DETAILED DESCRIPTION OF AN EMBODIMENT
FIG. 1 schematically illustrates an exemplary split compressor
turbine engine architecture 100. The engine includes a pair of
split compressors 112, 114 within a compressor section 110. The
compressors 112, 114 share an inlet 116, and operate in fluid
parallel, with the compressed air output being merged into a single
compressed airflow 122 downstream of both compressors 112, 114. The
inlet 116 draws ambient air from a surrounding atmosphere through a
first inlet 102 on a forward end of the engine 100 and through a
second inlet 104, on a radially outward surface of the engine
100.
Airflow into the engine follows flowpath 120, and branches into the
first inlet 102 along a first branch 124 and into the second inlet
104 along a second branch 126. The first and second branch 124, 126
merge at the compressor section 110 inlet 116, and the flow is then
split again between inlets of the first compressor 112 and the
second compressor 114. In some examples, the split is approximately
50%, with each compressor 112, 114 receiving approximately the same
volume of air along its respective flowpath as the other compressor
112, 114. Such an example can be achieved by providing each of the
compressors 112, 114 approximately equal sized inlets, thereby
ensure that an approximately equal volume of air will enter the
compressors 112, 114. In alternative examples, the compressors can
be sized such that different volumes of air are received at their
inlets, or a controlled or passive metering device can be
incorporated at the inlet 116.
Each compressor 112, 114 includes multiple compressor stages 118
that sequentially compress the air resulting in a higher pressure
at the compressor outlet than at the compressor inlet 116. Each
stage includes a compressor rotor and a corresponding compressor
stator, with the rotors being shaped to drive air along the
compressor as the rotors rotate. In some examples, the compressor
rotors are constructed of lightweight, high strength materials,
such as a lightweight high strength ceramic material. In further
examples, the light weight high strength ceramic material is a
silicon based structural material, such as silicon nitride, silicon
carbide, silicon carbide reinforced ceramic composite, or carbon
fiber reinforced silicon carbide composite.
The compressed airflow 122 is passed to a reverse flow combustor
130, where the compressed air is mixed with a fuel and ignited
according to known combustor techniques. The resultant combustion
products are passed along a combustion product flowpath 140 into a
turbine section 150.
Within the turbine section 150 are two single stage turbines 152,
154 arranged in fluid series. Each of the single stage turbines
152, 154 includes a single rotor 151, and a single stator vane 153.
In alternative examples, either or both of the turbines 152, 154
within the turbine section 150 can include multiple turbine stages,
instead of the illustrated single stage turbines 152, 154.
Each rotor 151 is connected to a corresponding shaft 160, 170. The
shafts 160, 170 are alternately referred to as spools. Each shaft
160, 170 connects the turbine rotor 151 to a corresponding one of
the compressors 112, 114, and drives the rotation of the
corresponding compressor 112, 114. In the example of FIG. 1, the
shafts 160, 170 are collinear, with the shaft 160 that is connected
to the forward turbine 154 being radially outward of the shaft 170
that is connected to the aft turbine 152. While illustrated in FIG.
1 utilizing direct drive connections to the shafts 160, 170, one of
skill in the art could adapt the engine architecture 100 to utilize
a geared connection, and drive one or both of the compressors 112,
114 via a geared connection.
Further, in the example of FIG. 1, the turbines 152, 154 are sized
such that rotation of the forward turbine 154, and rotation of the
aft turbine 152, drive rotation of their corresponding compressors
112, 114 at the same, or approximately the same, speed at any given
time.
In some examples, each of the compressors 112, 114 are driven to
rotate in the same direction about an engine centerline axis, and
are referred to as co-rotating compressors 112, 114. In alternative
examples, the compressors 112, 114 rotate in opposite directions
about the centerline axis, and are referred to as counter-rotating
compressors 112, 114. In either example, the turbine 152, 154
corresponding to a given compressor 112, 114 rotates in the same
direction as the compressor 112, 114.
With continued reference to FIG. 1, and with like numerals
indicating like elements, FIG. 2 schematically illustrates an
alternate configuration split compressor turbine engine
architecture 200. As with the first example, the architecture 200
includes two compressors 212, 214 arranged in parallel with an
inlet flow to a compressor section 210 being split between the
compressors 212, 214.
The output of the compressor section 210 is provided to a reverse
flow combustor 230, where the compressed air from the compressor
section 210 is mixed with a fuel and ignited. The resultant
combustion products are provided from the reverse flow combustor
230 to a turbine section 250 including a first turbine 254 and a
second turbine 252. Each of the turbines 252, 254 includes a single
stage having a stator 253 and a rotor 251. In alternative examples,
the turbines 252, 254 can include multiple stages and operate in a
similar fashion.
Each of the turbines 252, 254 is connected to a single shaft 260.
The shaft 260 is, in turn, connected to both of the compressors
212, 214 in either a direct drive (as illustrated) or a geared
connection. The shaft 260 translates rotation from the turbines
252, 254 to the compressors 212, 214, thereby allowing the turbines
252, 254 to drive rotation of the compressors 212, 214.
Aside from the alternate utilization of a single shaft 260, in
place of the two shaft 260, 270 arrangement of FIG. 1, the engine
architecture 200 of FIG. 2 operates, and is configured, in
fundamentally the same manner as the engine architecture of FIG. 1.
One of skill in the art, having the benefit of this disclosure will
understand the necessary adjustments required to configure the
engine architecture for a single shaft, as opposed to the two shaft
example described above in greater detail.
With continued reference to FIGS. 1 and 2, FIG. 3 illustrates a
method 300 for operating a split compressor turbine engine, such as
the engine architectures 100, 200 of FIGS. 1 and 2. Initially, an
airflow is provided to a split inlet, and is divided between two
parallel operating compressors within a compressor section in a
"Split Inlet Flow to Compressors" step 310.
The compressors operate in parallel to compress the air, and
provide an output of compressed air. The compressed air output from
each compressor is rejoined into a single compressed airflow in a
"Rejoin Compressed Airflow" step 320.
The rejoined compressed air is provided to a reverse flow combustor
and mixed with a fuel in the reverse flow combustor in a "Provide
Compressed Air to Reverse Flow Combustor" step 330. The fuel/air
mixture is ignited and the resultant combustion products are
expelled from the reverse flow combustor according to known reverse
flow combustor techniques.
The resultant combustion products are provided to a turbine section
and expanded across multiple turbines within the turbine section in
an "Expand Combustion Products Across Turbine" step 340. The
expansion of the combustion products drives the turbines to rotate,
and the rotation of the turbines is utilized to drive rotation of
at least one corresponding compressor via a shaft connection.
It is further understood that any of the above described concepts
can be used alone or in combination with any or all of the other
above described concepts. Although an embodiment of this invention
has been disclosed, a worker of ordinary skill in this art would
recognize that certain modifications would come within the scope of
this invention. For that reason, the following claims should be
studied to determine the true scope and content of this
invention.
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