U.S. patent application number 12/363427 was filed with the patent office on 2010-08-05 for gas turbine engine assembly and methods of assembling same.
Invention is credited to Thomas Ory Moniz, Robert Joseph Orlando, Alan Roy Stuart.
Application Number | 20100192595 12/363427 |
Document ID | / |
Family ID | 42124349 |
Filed Date | 2010-08-05 |
United States Patent
Application |
20100192595 |
Kind Code |
A1 |
Orlando; Robert Joseph ; et
al. |
August 5, 2010 |
GAS TURBINE ENGINE ASSEMBLY AND METHODS OF ASSEMBLING SAME
Abstract
A turbine engine assembly includes, a core gas turbine engine, a
first low-pressure turbine section in serial flow communication
with the core gas turbine engine, the first low-pressure turbine
section configured to rotate in a first rotational direction, a
first gear assembly coupled to the first low-pressure turbine
section, a second low-pressure turbine section coupled to the gear
assembly, the second low-pressure turbine section configured to
rotate in a second rotational direction, and a fan assembly coupled
to the second low-pressure turbine section.
Inventors: |
Orlando; Robert Joseph;
(West Chester, OH) ; Moniz; Thomas Ory; (Loveland,
OH) ; Stuart; Alan Roy; (Cincinnati, OH) |
Correspondence
Address: |
JOHN S. BEULICK (12729);C/O ARMSTRONG TEASDALE LLP
ONE METROPOLITAN SQUARE, SUITE 2600
ST. LOUIS
MO
63102-2740
US
|
Family ID: |
42124349 |
Appl. No.: |
12/363427 |
Filed: |
January 30, 2009 |
Current U.S.
Class: |
60/792 |
Current CPC
Class: |
Y10T 29/49229 20150115;
F02K 3/072 20130101; F02C 7/36 20130101; F05D 2220/323 20130101;
F05D 2220/327 20130101 |
Class at
Publication: |
60/792 |
International
Class: |
F02C 3/10 20060101
F02C003/10 |
Claims
1. A turbine engine assembly comprising; a core gas turbine engine;
a first low-pressure turbine section in serial flow communication
with said core gas turbine engine, said first low-pressure turbine
section configured to rotate in a first rotational direction; a
first gear assembly coupled to said first low-pressure turbine
section; a second low-pressure turbine section coupled to said gear
assembly, said second low-pressure turbine section configured to
rotate in a second rotational direction; and a fan assembly coupled
to said second low-pressure turbine section.
2. A turbine engine assembly in accordance with claim 1 further
comprising a booster compressor coupled to said second low-pressure
turbine section.
3. A turbine engine assembly in accordance with claim 1 wherein
said core gas turbine engine comprises a high pressure core.
4. A turbine engine assembly in accordance with claim 2 further
comprising a second gear assembly coupled between said booster
compressor and said second low-pressure turbine section.
5. A turbine engine assembly in accordance with claim 2 wherein
said booster compressor is configured to rotate in the second
direction.
6. A turbine engine assembly in accordance with claim 1 wherein
said fan assembly comprises a single stage fan.
7. A turbine engine assembly in accordance with claim 1 wherein
said first direction is opposite said second direction.
8. A turbine engine assembly in accordance with claim 1 wherein
said fan assembly is configured to rotate in said second rotational
direction.
9. A method for assembling a gas turbine engine, the method
comprising: coupling a first section of a low pressure turbine
downstream of a core gas turbine engine, wherein the first section
of the low pressure turbine rotates in a first direction; coupling
a first gear assembly to the first section of the low pressure
turbine; coupling a second section of the low pressure turbine to
the first gear assembly, wherein the second section of the low
pressure turbine rotates in a second direction; and coupling a
single stage fan assembly to the second section of the low pressure
turbine.
10. A method in accordance with claim 9 further comprising:
coupling a second gear assembly to said fan assembly; and coupling
a booster compressor to the second gear assembly.
11. A method in accordance with claim 9 further comprising coupling
a booster compressor to the second section of the low-pressure
turbine.
12. A method in accordance with claim 9 wherein coupling a first
stage of a low pressure turbine to a core turbine engine further
comprises coupling a first stage of a low pressure turbine to a
high pressure ratio core turbine engine.
13. A method in accordance with claim 9 wherein coupling a single
stage fan assembly to the second section of the low pressure
turbine engine further comprises coupling a single stage fan
assembly configured to rotate in a second direction to the second
section of the low pressure turbine engine.
14. A method in accordance with claim 11 wherein coupling a booster
compressor to the second section of the low-pressure turbine
further comprises coupling the booster compressor configured to
rotate in the second direction to the second section of the
low-pressure turbine.
15. A gas turbine engine assembly comprising: a core gas turbine
engine; a first low-pressure turbine section in serial flow
communication with said core gas turbine engine; a second
low-pressure turbine section in serial flow communication with said
core gas turbine engine aft of said first low-pressure turbine
section; a fan assembly coupled to said second low-pressure turbine
section; a booster compressor coupled to said first low-pressure
turbine section; and a gear assembly coupled between said booster
compressor and said fan assembly.
16. A gas turbine engine assembly in accordance with claim 15
wherein said booster compressor rotates in a first direction and
said second low-pressure turbine section rotates in a second
direction, opposite the first direction.
17. A gas turbine engine assembly in accordance with claim 15
wherein said booster compressor is coupled to said first
low-pressure turbine section via a first drive shaft and said fan
assembly is coupled to said second low-pressure turbine section via
a second drive shaft.
18. A gas turbine engine assembly in accordance with claim 15
wherein said booster compressor rotates at a first rotational speed
and said second low pressure turbine section rotates at a second
rotational speed, wherein the first rotational speed is
substantially faster than the second rotational speed.
19. A gas turbine engine assembly in accordance with claim 15
wherein said fan assembly comprises a single stage fan assembly.
Description
BACKGROUND OF THE INVENTION
[0001] This invention relates generally to gas turbine engines, and
more specifically to gas turbine engine assemblies and methods of
assembling the same.
[0002] At least some known gas turbine engines include a fan, a
core engine, and a power turbine. The core engine includes at least
one compressor, a combustor, a high-pressure turbine and a
low-pressure turbine coupled together in a serial flow
relationship. More specifically, the compressor and high-pressure
turbine are coupled through a shaft to define a high-pressure rotor
assembly. Air entering the core engine is mixed with fuel and
ignited to form a high energy gas stream. The high energy gas
stream flows through the high-pressure turbine to rotatably drive
the high-pressure turbine such that the shaft, in turn, rotatably
drives the compressor.
[0003] The gas stream expands as it flows through the low-pressure
turbine positioned aft of the high-pressure turbine. The
low-pressure turbine includes a rotor assembly having a fan coupled
to a drive shaft. The low-pressure turbine rotatably drives the fan
through the drive shaft.
[0004] Modern commercial turbofans tend toward higher bypass ratios
to improve efficiency. For acoustic and fan efficiency reasons, it
is desirable to reduce fan RPM or tip speed. However, a lower RPM
increases low-pressure turbine loading, diameter and/or stage
count. A fan directly driven by the low-pressure turbine limits the
choice in fan speed because a slight reduction in fan speed for
improved performance results in poorer performance in the
low-pressure turbine.
BRIEF DESCRIPTION OF THE INVENTION
[0005] In one aspect, a turbine engine assembly including, a core
gas turbine engine, a first low-pressure turbine section in serial
flow communication with the core gas turbine engine, the first
low-pressure turbine section configured to rotate in a first
rotational direction, a first gear assembly coupled to the first
low-pressure turbine section, a second low-pressure turbine section
coupled to the gear assembly, the second low-pressure turbine
section configured to rotate in a second rotational direction, and
a fan assembly coupled to the second low-pressure turbine
section.
[0006] In another aspect, a method for assembling a gas turbine
engine including, coupling a first section of a low pressure
turbine downstream of a core gas turbine engine, wherein the first
section of the low pressure turbine rotates in a first direction,
coupling a first gear assembly to the first stage of the low
pressure turbine, coupling a second section of the low pressure
turbine to the first gear assembly, wherein the second section of
the low pressure turbine rotates in a second direction, and
coupling a single stage fan assembly to the second section of the
low pressure turbine.
[0007] In a further aspect, a gas turbine engine assembly
including, a core gas turbine engine, a first low-pressure turbine
section in serial flow communication with the core gas turbine
engine, a second low-pressure turbine section in serial flow
communication with the core gas turbine engine aft of the first
low-pressure turbine section, a fan assembly coupled to the second
low-pressure turbine section, a booster compressor coupled to the
first low-pressure turbine section, and a gear assembly coupled
between said booster compressor and said fan assembly.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] FIGS. 1-5 show exemplary embodiments of the assembly and
method described herein.
[0009] FIG. 1 is a cross-sectional view of an exemplary turbine
engine assembly;
[0010] FIG. 2 is a simplified representation of one embodiment of a
turbine engine assembly in accordance with the present
invention;
[0011] FIG. 3 is a simplified representation of one embodiment of a
turbine engine assembly in accordance with the present invention;
and
[0012] FIG. 4 is a simplified representation of an additional
embodiment of a turbine engine assembly in accordance with the
present invention; and
[0013] FIG. 5 is a simplified representation of an additional
embodiment of a turbine engine assembly in accordance with the
present invention.
DETAILED DESCRIPTION OF THE INVENTION
[0014] FIG. 1 is a cross-sectional view of a portion of an
exemplary turbine engine assembly 10 having a longitudinal axis 11.
In the exemplary embodiment, turbine engine assembly 10 includes a
core gas turbine engine 12 generally defined by a casing 13. A
low-pressure turbine 14 is coupled axially aft of core gas turbine
engine 12 and a single-stage fan assembly 16 is coupled axially
forward of core gas turbine engine 12.
[0015] Core gas turbine engine 12 includes an outer casing 20 that
defines an annular core engine inlet 22. Casing 20 surrounds a
low-pressure booster compressor 24. Single-stage fan assembly 16
increases the pressure of incoming air to a first pressure level
and directs a portion of the incoming air to the low-pressure
booster compressor 24. Low-pressure booster compressor 24 receives
air from the single-stage fan assembly 16 and facilitates
increasing the pressure to a higher, second pressure level. In one
embodiment, core gas turbine engine 12 is a core CFM56 gas turbine
engine available from General Electric Aircraft Engines,
Cincinnati, Ohio. In another embodiment a high pressure core is
used and the booster is not.
[0016] In some embodiments, a high-pressure, multi-stage,
axial-flow compressor 26 receives pressurized air from booster
compressor 24 and further increases the pressure of the air to a
third, higher pressure level. The high-pressure air is channeled to
a combustor 28 and is mixed with fuel. The fuel-air mixture is
ignited to raise the temperature and energy level of the
pressurized air. The high energy combustion products flow to a
first or high-pressure turbine 30 for driving compressor 26 through
a first rotatable drive shaft 32, and then to second or
low-pressure turbine 14. After driving low-pressure turbine 14, the
combustion products leave turbine engine assembly 10 through an
exhaust nozzle (not shown) to provide propulsive jet thrust.
[0017] In one embodiment, booster compressor 24 includes a
plurality of rows of rotor blades 70 that are coupled to a
respective rotor disk 72. Booster compressor 24 is positioned aft
of an inlet guide vane assembly 74 and is coupled to a drive shaft
34 such that booster compressor 24 rotates at a rotational speed
that is substantially equal to a rotational speed of fan assembly
16. Although booster compressor 24 is shown as having only three
rows of rotor blades 70, booster compressor 24 may have any
suitable number and/or rows of rotor blades 70, such as a single
row of rotor blades 70 or a plurality of rows of rotor blades 70
that are interdigitated with a plurality of rows of guide vanes 76.
In one embodiment, guide vanes 76 are fixedly or securely coupled
to a booster case 78. In an alternative embodiment, rotor blades 70
are rotatably coupled to rotor disk 72 such that guide vanes 76 are
movable during engine operation to facilitate varying a quantity of
air channeled through booster compressor 24. In another alternative
embodiment, turbine engine assembly 10 does not include booster
compressor 24.
[0018] Low-pressure turbine 14 includes two sections, a first
section 80 and a second section 82. Although first section 80 is
shown with one stage and second section 82 is shown with two stages
each section may have multiple or single stages in other
embodiments. First section 80 is coupled to a first intermediate
drive shaft 84 and rotates in a first direction with a first
rotational speed while second section 82 is coupled to a second
intermediate drive shaft 86 and rotates in a second direction with
a second rotational speed. Both first and second intermediate drive
shafts 84 and 86 are coupled to second rotatable drive shaft 34
through a gear assembly 88. In the exemplary embodiment gear
assembly 88 is a planetary (star type) reversing and speed reducing
gear assembly. In other embodiments, gear assembly 88 may be any
other type of gear assembly.
[0019] Second rotatable drive shaft 34 drives fan assembly 16. Fan
assembly 16 is configured to rotate about longitudinal axis 11 in a
second rotational direction, includes at least one row of rotor
blades 60, and is positioned within a fan case 64. Rotor blades 60
are coupled to a rotor disk 66.
[0020] FIG. 2 describes one embodiment of the claimed invention. In
the exemplary embodiment, gas turbine engine 100 includes a
compressor 102, a core gas engine 104, a high pressure turbine 110
and a low-pressure turbine 114 in serial flow arrangement. High
pressure turbine 110 drives compressor 102 through a first
rotatable shaft 112. Low pressure turbine 114 includes two
sections, a first section 116 and a second section 118. Although
not shown, the first section 116 and the second section 118 may
have multiple or single stages in various embodiments. First
section 116 is coupled to a first intermediate drive shaft (not
shown) and rotates in a first direction with a first rotational
speed while second section 118 is coupled to a second intermediate
drive shaft (not shown) and rotates in a second direction with a
second rotational speed. Both first and second intermediate drive
shafts (not shown) are coupled to second rotatable drive shaft 120
through a gear assembly 122. Second rotatable drive shaft 120
drives a fan assembly 124 and a low-pressure booster compressor
126. Fan assembly 124 is configured to rotate about longitudinal
axis 111 in a second rotational direction.
[0021] FIG. 3 describes another embodiment where a low pressure
turbine 314 is divided into a first section 316 and a second
section 318. First section 316 and second section 318 are coupled
to a second rotatable drive shaft 320 through a first gear assembly
322. Second rotatable drive shaft 320 is coupled to and directly
drives fan assembly 324. Second rotatable drive shaft 320 also
drives the booster 326 through a second gear assembly 328.
[0022] FIG. 4 describes still another embodiment where a low
pressure turbine 414 is divided into a first section 416 and a
second section 418. First section 416 couples directly to a second
rotatable drive shaft 420 that directly drives a booster compressor
424 and drives a fan assembly 426 through a gear assembly 428.
Second section 418 couples directly to a third rotatable drive
shaft 430 that couples directly to and drives fan assembly 416.
[0023] FIG. 5 describes still another embodiment where a high
pressure core engine 508 is coupled to a high pressure turbine 510
through a first rotatable drive shaft 512. Low pressure turbine 514
is located axially aft of the high pressure turbine 510 and is
divided into a first section 516 and a second section 518. First
section 516 and second section 518 are coupled to a second
rotatable drive shaft 520 through a first gear assembly 522. Second
rotatable drive shaft 520 is coupled to and directly drives fan
assembly 524.
[0024] Exemplary embodiments of a gas turbine engine assembly and
methods of assembly the gas turbine engine assembly are described
above in detail. The assembly and method are not limited to the
specific embodiments described herein, but rather, components of
the assembly and/or steps of the method may be utilized
independently and separately from other components and/or steps
described herein. Further, the described assembly components and/or
the method steps can also be defined in, or used in combination
with, other assemblies and/or methods, and are not limited to
practice with only the assembly and/or method as described
herein.
[0025] This written description uses examples to disclose the
invention, including the best mode, and also to enable any person
skilled in the art to make and use the invention. The patentable
scope of the invention is defined by the claims, and may include
other examples that occur to those skilled in the art. Such other
examples are intended to be within the scope of the claims if they
have structural elements that do not differ from the literal
language of the claims, or if they include equivalent structural
elements with insubstantial differences from the literal languages
of the claims.
* * * * *