PLASMA ENHANCED COMPRESSOR DUCT
A compression system is disclosed, comprising a first compressor having a first flowpath, a second compressor having a second flowpath located axially aft from the first compressor, and a transition duct capable of flowing an airfow from the first compressor to the second compressor, the transition duct having at least one plasma actuator mounted in the transition duct.
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This invention relates generally to compressors, and more specifically to a compression system having a transition duct having plasma actuators.
In a gas turbine engine, air is pressurized in a compression module during operation. The air channeled through the compression module is mixed with fuel in a combustor and ignited, generating hot combustion gases which flow through turbine stages that extract energy therefrom for powering the fan and compressor rotors and generate engine thrust to propel an aircraft in flight or to power a load, such as an electrical generator.
The compressor includes a rotor assembly and a stator assembly. The rotor assembly includes a plurality of rotor blades extending radially outward from a disk. More specifically, each rotor blade extends radially between a platform adjacent the disk, to a tip. A gas flowpath through the rotor assembly is bound radially inward by the rotor blade platforms, and radially outward by a plurality of shrouds.
The stator assembly includes a plurality of circumferentially spaced apart stator vanes or airfoils that direct the compressed gas entering the compressor to the rotor blades. The stator vanes extend radially between an inner band and an outer band. A gas flowpath through the stator assembly is bound radially inward by the inner bands, and radially outward by outer bands. The rotor stages comprise rotor blades arranged circumferentially around a rotor hub. Each compression stage comprises a vane stage and a rotor stage.
Modern high by-pass ratio gas turbine engines have a booster (low pressure compressor) and a high pressure compressor with a transition duct located in between. Conventional transition or gooseneck duct geometries are governed by their levels of endwall curvature, since excessive curvature leads to endwall boundary layer separation and therefore high losses in efficiency. To ensure a smooth aerodynamic transition without flow separation, conventional transition duct designs must have some minimum axial length for a given change in annular flow radius. This is not desirable because increased transition duct lengths translate directly to increased engine length, which in turn adds engine weight and reduces backbone stiffness of the engine. This reduction in stiffness makes it more difficult to maintain the desired clearances over the rotor tips, reducing the efficiency and operability range of the engine.
As compressor and booster rotors approach the limits of their capability to add work/pressure to the air, they tend to become less efficient and, if pushed beyond this limit, stall (fail to produce their required pressure rise, leading to reversed flow through the stage and a loss of engine thrust). A booster rotor that is designed very near to its limits in the rear stages of the booster could experience significant operability problems. This is a concern in conventional booster system designs which are limited to lower radii in the aft rotor stages. These could be corrected by pushing the back end of the booster outwards, as enabled by the use of plasma actuators in the transition duct.
Accordingly, it is would be desirable to have a shorter transition duct design having enhanced pressure distribution without causing flow separation in the duct. It would be desirable to have a booster system which has a higher radius for aft rotor stages without causing flow separation in the transition duct.
BRIEF DESCRIPTION OF THE INVENTIONThe above-mentioned needs may be met by exemplary embodiments which provide a compression system comprising a first compressor having a first flowpath, a second compressor having a second flowpath located axially aft from the first compressor, and a transition duct capable of flowing an airfow from the first compressor to the second compressor, the transition duct having at least one plasma actuator mounted in the transition duct.
In another aspect of the present invention, a duct comprises an inlet portion, an exit portion located at a distance axially aft from the inlet portion, an axially arcuate inner wall extending between the inlet portion and the exit portion, an axially arcuate outer wall extending between the inlet portion and the exit portion, an axially arcuate flowpath between the inner wall and the outer wall, and at least one plasma actuator mounted in the duct.
In another aspect of the present invention, a gas turbine engine comprises a duct located between a first compressor and a second compressor, the duct having at least one plasma actuator mounted in the duct.
The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the concluding part of the specification. The invention, however, may be best understood by reference to the following description taken in conjunction with the accompanying drawing figures in which:
Referring to the drawings wherein identical reference numerals denote the same elements throughout the various views,
In operation, air flows through fan assembly blades 17 and a portion of that air flows as bypass airflow 15 and a portion of the air flows as core airflow 25 into the compression system 20 that includes a first compressor 21 and a second compressor 22. In the exemplary embodiments shown in
In the exemplary embodiments shown in
Referring to
As is evident from the exemplary embodiments shown herein, the inner wall 31 and outer wall 32 have significant curvatures in the axial direction. In the exemplary embodiments of the present invention shown in
The exemplary embodiment shown in
In the exemplary embodiment of the present invention shown in
The exemplary booster system 50 shown in
A gas turbine engine 10 having a booster system 50 with the gooseneck duct 38 having plasma actuators as described herein, can be operated by energizing the first electrode 64 and second electrode 66 using the AC potential from the AC power supply 70. By energizing the electrodes 64, 66 and creating the plasma 80, flow separation in the duct 38 can be reduced which results in the advantages and improvements in pressure distributions in the booster system 50. In one method, the plasma actuators, such as item 60 in
As used herein, an element or step recited in the singular and proceeded with the word “a” or “an” should be understood as not excluding plural said elements or steps, unless such exclusion is explicitly recited. When introducing elements/components/steps etc. of designing and/or manufacturing components and systems described and/or illustrated herein, the articles “a”, “an”, “the” and “said” are intended to mean that there are one or more of the element(s)/component(s)/etc. The terms “comprising”, “including” and “having” are intended to be inclusive and mean that there may be additional element(s)/component(s)/etc. other than the listed element(s)/component(s)/etc. Furthermore, references to “one embodiment” of the present invention are not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the recited features.
Although the methods and articles such as vanes, outer bands, inner bands and vane segments described herein are described in the context of a compressor used in a turbine engine, it is understood that the vanes and vane segments and methods of their manufacture or repair described herein are not limited to compressors or turbine engines. The vanes and vane segments illustrated in the figures included herein are not limited to the specific embodiments described herein, but rather, these can be utilized independently and separately from other components described herein.
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.
While there have been described herein what are considered to be preferred and exemplary embodiments of the present invention, other modifications of the invention shall be apparent to those skilled in the art from the teachings herein, and it is, therefore, desired to be secured in the appended claims all such modifications as fall within the true spirit and scope of the invention.
Claims
1. A compression system comprising:
- a first compressor having a first flowpath;
- a second compressor located axially aft from the first compressor, the second compressor having a second flowpath; and
- a transition duct located between the first compressor and the second compressor capable of flowing an airfow from the first compressor to the second compressor, the transition duct having at least one plasma actuator mounted in the transition duct.
2. A compression system according to claim 1 wherein at least a portion of the second flowpath is located radially inward from a portion of the first flowpath.
3. A compression system according to claim 1 wherein the first compressor is a booster having a row of booster blades arranged in a circumferential direction around a longitudinal axis.
4. A compression system according to claim 3 wherein the second compressor is an axial-flow compressor having a row of compressor blades arranged in a circumferential direction around the longitudinal axis.
5. A compression system according to claim 1 wherein the transition duct comprises an axially arcuate inner wall and an axially arcuate outer wall.
6. A compression system according to claim 5 wherein the inner wall and outer wall form a third flowpath having an inlet portion and an exit portion located at a distance axially aft from the inlet portion.
7. A compression system according to claim 6 wherein the inlet portion has an inlet area and the exit portion has an exit area that is greater than the inlet area.
8. A compression system according to claim 5 wherein the at least one plasma actuator is located on the inner wall.
9. A compression system according to claim 5 wherein the at least one plasma actuator is located on the outer wall.
10. A compression system according to claim 1 further comprising an outlet guide vane located between the first compressor and the transition duct wherein the outlet guide vane comprises a hub portion having a plasma actuator located on the hub portion.
11. A compression system according to claim 1 wherein the plasma actuator is continuous in a circumferential direction around a longitudinal axis.
12. A compression system according to claim 1 further comprising a plurality of plasma actuators arranged in a circumferential direction around a longitudinal axis.
13. A compression system according to claim 1 wherein the plasma actuator comprises a first electrode and a second electrode separated by a dielectric material.
14. A compression system according to claim 13 further comprising an AC power supply connected to the first electrode and the second electrode to supply a high voltage AC potential to the first electrode and the second electrode.
15. A duct comprising:
- an inlet portion;
- an exit portion located at a distance axially aft from the inlet portion;
- an axially arcuate inner wall extending between the inlet portion and the exit portion;
- an axially arcuate outer wall extending between the inlet portion and the exit portion;
- an axially arcuate flowpath between the inner wall and the outer wall; and
- at least one plasma actuator mounted in the duct.
16. A duct according to claim 15 wherein the inlet portion has an inlet area and the exit portion has an exit area that is greater than the inlet area.
17. A duct according to claim 15 wherein the at least one plasma actuator is located on the inner wall.
18. A duct according to claim 15 wherein the at least one plasma actuator is located on the outer wall.
19. A duct according to claim 15 wherein the plasma actuator comprises a first electrode and a second electrode separated by a dielectric material.
20. A duct according to claim 13 further comprising an AC power supply connected to the first electrode and the second electrode to supply a high voltage AC potential to the first electrode and the second electrode.
21. A gas turbine engine comprising a duct located between a first compressor and a second compressor, the duct having at least one plasma actuator mounted in the duct.
Type: Application
Filed: Jan 8, 2009
Publication Date: Jul 8, 2010
Applicant:
Inventors: DAVID SCOTT CLARK (Liberty Township, OH), Aspi Rustom Wadia (Loveland, OH), Ching Pang Lee (Cincinnati, OH)
Application Number: 12/350,420
International Classification: F04D 29/58 (20060101); F04D 29/52 (20060101);