US20110271654A1 - Diffuser for gas turbine system - Google Patents
Diffuser for gas turbine system Download PDFInfo
- Publication number
- US20110271654A1 US20110271654A1 US12/774,262 US77426210A US2011271654A1 US 20110271654 A1 US20110271654 A1 US 20110271654A1 US 77426210 A US77426210 A US 77426210A US 2011271654 A1 US2011271654 A1 US 2011271654A1
- Authority
- US
- United States
- Prior art keywords
- diffuser
- gas flow
- generally
- ducts
- flow
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/545—Ducts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
Definitions
- the subject matter disclosed herein related generally to gas turbine systems, and more particularly to diffusers in gas turbine systems.
- a conventional gas turbine system includes a compressor section, a combustor section, and at least one turbine section.
- the compressor section is configured to compress air as the air flows through the compressor section.
- the air is then flowed from the compressor section to the combustor section, where it is mixed with fuel and combusted, generating a hot gas flow.
- the hot gas flow is provided to the turbine section, which utilizes the hot gas flow by extracting energy from it to power the compressor, an electrical generator, and other various loads.
- typical known compressor sections include an axial diffuser 19 , as shown in FIG. 2 , which acts to reduce the velocity of the air flow exiting the compressor section.
- known diffusers typically diffuse the air flow as the air flow travels along a generally longitudinal axis 90 of the gas turbine system.
- the air flow exiting the compressor section generally has an “exit swirl” component, meaning that the air flow is traveling in a generally rotational direction, with tangential and radial flow components, along with traveling in a generally longitudinal direction.
- a guide vane or guide vanes 28 are typically disposed upstream of the axial diffuser 19 in the compressor section. The guide vanes 28 are designed to reduce the exit swirl.
- a diffuser that reduces air flow pressure drops would be desired in the art. Additionally, a diffuser that utilizes the exit swirl associated with the air flow to guide the air flow to the combustor section would be advantageous. Further, a diffuser that eliminates the need for guide vanes in the compressor section would be desired.
- a diffuser for a gas turbine system having a longitudinal axis includes a plurality of diffuser ducts.
- Each of the plurality of diffuser ducts is disposed annularly about the longitudinal axis and has an inlet, an outlet, and a passage extending between the inlet and the outlet.
- the outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct.
- Each of the plurality of diffuser ducts is configured to flow a gas flow therethrough, reducing the gas flow velocity.
- FIG. 1 is a schematic view of a gas turbine system of the present disclosure
- FIG. 2 is a cross-sectional view of a known gas turbine system
- FIG. 3 is an exploded perspective view of one embodiment of a diffuser of the present disclosure
- FIG. 4 is a perspective view of one embodiment of a diffuser duct of the present disclosure.
- FIG. 5 is a front view of one embodiment of a diffuser of the present disclosure.
- FIG. 6 is a front view of another embodiment of a diffuser of the present disclosure.
- FIG. 1 is a schematic diagram of a gas turbine system 10 .
- the system 10 may include a compressor section 12 , a combustor section 14 , and a turbine section 16 . Further, the system 10 may include a plurality of compressor sections 12 , combustor sections 14 , and turbine sections 16 .
- the compressor section 12 and turbine section 16 may be coupled by a shaft 18 .
- the shaft 18 may be a single shaft or a plurality of shaft segments coupled together to form shaft 18 .
- the gas turbine system 10 may have a central longitudinal axis 90 . For example, the shaft 18 may be disposed longitudinally along the axis 90 .
- the compressor section 12 may compress a gas flow 80 as the gas flow 80 flows through the compressor section 12 .
- the gas flow 80 may be, for example, air or any other suitable gas.
- the compressor section 12 may then flow the gas flow 80 to the combustor section 14 , which may be configured to accept the gas flow 80 , as discussed below.
- the gas flow 80 may flow in a generally longitudinal direction with respect to the longitudinal axis 90 .
- the gas flow 80 may generally further include other flow components.
- the gas flow 80 after being compressed may have flow components known collectively in the art as an “exit swirl.”
- the gas flow 80 may flow in a generally tangential direction, and may further flow in a generally radial direction.
- the compressor section 12 may include at least one guide vane 28 .
- the guide vane 28 may reduce the exit swirl, thus reducing the tangential and radial flow components of the gas flow 80 .
- the compressor section 12 may be free from guide vanes 28 .
- the compressor section 12 may include a diffuser 20 .
- the diffuser 20 may be configured to reduce the velocity of the gas flow 80 , as discussed below.
- the diffuser 20 may further generally flow the gas flow 80 to the combustor section 14 .
- gas flow 80 may flow through the diffuser 20 and be provided to the combustor section 14 .
- the gas flow 80 may exit the diffuser 20 into a plenum 22 .
- the gas flow 80 may then be provided from the plenum 22 to the combustor section 14 .
- the gas flow 80 may exit the diffuser 20 directly into the combustor section 14 .
- the combustor section 14 may include a plurality of combustor cans 24 .
- the diffuser 20 may comprise a plurality of diffuser ducts 30 .
- Each of the diffuser ducts 30 may be coupled with a combustor can 24 .
- the combustor cans 24 may be configured to accept gas flow 80 from one of the plurality of diffuser ducts 30 .
- each of the combustor cans 24 may be fluidly connected to one of the diffuser ducts 30 , such that gas flow 80 exiting the diffuser ducts 30 immediately enters the combustor cans 24 , and thus the combustor section 14 .
- the diffuser 20 of the present disclosure includes a plurality of diffuser ducts 30 .
- each of the plurality of diffuser ducts 30 may have an inlet 32 , an outlet 36 , and a passage extending between the inlet 32 and the outlet 36 .
- the diffuser ducts 30 may be configured to flow a gas flow 80 therethrough, reducing the gas flow 80 velocity.
- the inlet 32 of each of the plurality of diffuser ducts 30 may have a cross-sectional area that is generally smaller than the cross-sectional area of the outlet 36 of the respective diffuser duct 30 .
- the inlets 32 and outlets 36 may have generally circular or oval cross-sections, rectangular cross-sections, triangular cross-sections, or any other suitable polygonal cross-sections. Further, it should be understood that the inlet 32 and outlet 34 of a respective diffuser duct 30 need not have similarly shaped cross-sections. For example, in one embodiment, the inlet 32 may have a generally rectangular cross-section, while the outlet 36 may have a generally circular cross-section.
- the passage 34 may be generally tapered between the inlet 32 and the outlet 36 .
- the passage 34 may be generally conically shaped.
- the passage 34 may have a generally rectangular cross-section, triangular cross-section, or any other suitable polygonal cross-section. It should be understood that the cross-sectional shape of the passage 34 may change throughout the passage 34 as the passage 34 tapers from the relatively smaller inlet 32 to the relatively larger outlet 36 .
- the diffuser ducts 30 may be disposed in an annular array about the longitudinal axis 90 .
- the gas flow 80 may flow through the inlets 32 into the annular array of diffuser ducts 30 .
- the outlet 36 of each of the plurality of diffuser ducts 30 may be offset from the inlet 32 of the respective diffuser duct 30 .
- offset means spaced from along the identified coordinate direction.
- the outlet 36 of each of the plurality of diffuser ducts 30 may be tangentially offset from the inlet 32 of the respective diffuser duct 30 , such as offset along a tangential axis 92 . Because the outlet 36 of each of the plurality of diffuser ducts 30 is tangentially offset from the inlet 32 of the respective diffuser duct 30 , the diffuser ducts 30 may advantageously utilize the tangential component of the gas flow 80 exit swirl to flow the gas flow 80 through the diffuser duets 30 .
- this utilization of the tangential gas flow 80 component may eliminate the need for guide vanes 28 in the compressor section 12 . Further, the utilization of the tangential gas flow 80 component may prevent gas flow 80 pressure losses due to flow direction changes in typical prior art gas turbine systems as the gas flow 80 flows from the compressor section 12 through the diffuser 20 to the combustor section 14 .
- the outlet 36 of each of the plurality of diffuser ducts 30 may be longitudinally offset from the inlet 32 of the respective diffuser duct 30 , such as offset along the longitudinal axis 90 . Because the outlet 36 of each of the plurality of diffuser ducts 30 is longitudinally offset from the inlet 32 of the respective diffuser duct 30 , the diffuser ducts 30 may advantageously utilize the longitudinal component of the gas flow 80 to flow the gas flow 80 through the diffuser ducts 30 .
- the outlet 36 of each of the plurality of diffuser ducts 30 may be radially offset from the inlet 32 of the respective diffuser duct 30 , such as offset along a radial axis 94 . Because the outlet 36 of each of the plurality of diffuser ducts 30 is radially offset from the inlet 32 of the respective diffuser duct 30 , the diffuser ducts 30 may advantageously utilize the radial component of the gas flow 80 exit swirl to flow the gas flow 80 through the diffuser ducts 30 .
- the tangential axis 92 and the radial axis 94 are defined individually for each diffuser duct 30 with respect to the circumference defined by the diffuser 20 and diffuser ducts 30 , as shown in FIGS. 5 and 6 , and that the axes 92 and 94 vary for each diffuser duct 30 about the circumference of the diffuser 20 based on the number of diffuser ducts 30 disposed in an annular array about the longitudinal axis 90 of the diffuser 20 .
- Each of the passages 34 may include a first guide portion 40 , as shown in FIG. 4 .
- the first guide portion 40 may be disposed adjacent the inlet 32 of the respective diffuser duct 30 .
- the first guide portion 40 may be any portion of the passage 34 of the diffuser duct 30 .
- the first guide portion 40 may be that portion of the passage 34 that redirects the general direction of gas flow 80 within a diffuser duct 30 .
- the first guide portions 40 may be configured to guide the gas flow 80 from a generally longitudinal flow direction to a generally tangential flow direction.
- the first guide portions 40 may be configured to guide the gas flow 80 from a generally longitudinal flow direction to a generally radial flow direction, a generally tangential and radial flow direction, a generally tangential and longitudinal flow direction, or to a generally tangential, radial, and longitudinal flow direction.
- gas flow 80 in any general direction, such as in a generally longitudinal direction may have other flow components, such as radial and tangential flow components, and is not limited to flow strictly in the referenced direction.
- the gas flow 80 may continue to flow through the passage 34 towards the outlet 36 .
- the passages 34 may extend in a generally linear manner downstream of the guide portion 40 with respect to the gas flow 80 , as shown in FIG. 6 .
- the gas flow 80 after passing through the first guide portion 40 of the passage 34 , may continue through the passage 34 in a generally linear manner.
- the passages 34 may extend in a generally curvilinear manner downstream of the guide portion 40 with respect to the gas flow 80 , as shown in FIGS. 3 through 5 .
- the gas flow 80 after passing through the first guide portion 40 of the passage 34 , may continue through the passage 34 in a generally curvilinear manner.
- Each of the passages 34 may further include a second guide portion 42 .
- the second guide portion 42 may be disposed adjacent the outlet 36 of the respective diffuser duct 30 .
- the second guide portion 42 may be any portion of the passage 34 of the diffuser duct 30 .
- the second guide portion 42 may be another portion of the passage 34 that further redirects the general direction of gas flow 80 within a diffuser duct 30 .
- the second guide portions 42 may be configured to guide the gas flow 80 from a generally tangential flow direction to a generally longitudinal flow direction.
- the second guide portions 42 may be configured to guide the gas flow 80 from a generally radial flow direction, a generally tangential and radial flow direction, a generally tangential and longitudinal flow direction, or a generally tangential, radial, and longitudinal flow direction to a generally longitudinal flow direction.
- gas flow 80 in any general direction, such as in a generally longitudinal direction may have other flow components, such as radial and tangential flow components, and is not limited to flow strictly in the referenced direction.
- the gas flow 80 may flow through the passage 34 towards the guide portion 42 and the outlet 36 .
- the passages 34 may extend in a generally linear manner upstream of the second guide portion 42 with respect to the gas flow 80 , as shown in FIG. 6 .
- the gas flow 80 before passing through the second guide portion 42 of the passage 34 , may travel through the passage 34 in a generally linear manner.
- the passages 34 may extend in a generally curvilinear manner upstream of the second guide portion 42 with respect to the gas flow 80 , as shown in FIGS. 3 through 5 .
- the gas flow 80 before passing through the second guide portion 42 of the passage 34 , may travel through the passage 34 in a generally curvilinear manner.
- the gas flow 80 may exit the diffuser 20 .
- the gas flow 80 may exit the diffuser 20 flowing in a generally tangential direction. It should be understood, however, that the gas flow 80 may have radial and longitudinal flow components, and is not limited to flow in a strictly tangential direction.
- the gas flow 80 may exit the diffuser 20 flowing in a generally longitudinal direction. It should be understood, however, that the gas flow 80 may have tangential and radial flow components, and is not limited to flow in a strictly longitudinal direction. Further, the gas flow 80 may exit the diffuser 20 flowing in a generally radial direction. It should be understood, however, that the gas flow 80 may have tangential and longitudinal flow components, and is not limited to flow in a strictly radial direction.
- the gas flow 80 may enter a plenum 22 , or may directly enter the combustor section 14 .
- each of the diffuser ducts 30 may be coupled to a combustor can 24 , and the gas flow 80 exiting each diffuser duct 30 may enter the combustor can 24 coupled with the diffuser duct 30 .
- the diffuser 20 may include a number of diffuser ducts 20 equal to the number of combustor cans 24 in the combustor 14 .
- the diffuser 20 in various embodiments, may include 8, 12, or 16 diffuser ducts 30 , or any other suitable number of diffuser ducts 30 .
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A diffuser for a gas turbine system having a longitudinal axis is disclosed. The diffuser includes a plurality of diffuser ducts. Each of the plurality of diffuser ducts is disposed annularly about the longitudinal axis and has an inlet, an outlet, and a passage extending between the inlet and the outlet. The outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct. Each of the plurality of diffuser ducts is configured to flow a gas flow therethrough, reducing the gas flow velocity.
Description
- The subject matter disclosed herein related generally to gas turbine systems, and more particularly to diffusers in gas turbine systems.
- Gas turbine systems are widely utilized in fields such as power generation. A conventional gas turbine system includes a compressor section, a combustor section, and at least one turbine section. The compressor section is configured to compress air as the air flows through the compressor section. The air is then flowed from the compressor section to the combustor section, where it is mixed with fuel and combusted, generating a hot gas flow. The hot gas flow is provided to the turbine section, which utilizes the hot gas flow by extracting energy from it to power the compressor, an electrical generator, and other various loads.
- In conventional gas turbine systems, the air flow compressed in the compressor section is discharged from the compressor section at a relatively high velocity. The velocity of this air flow generally should be reduced to a velocity that is optimal for entering the combustor section. Thus, typical known compressor sections include an
axial diffuser 19, as shown inFIG. 2 , which acts to reduce the velocity of the air flow exiting the compressor section. - The utilization of typical known diffusers in gas turbine systems can subject the gas turbine system to a variety of problems. For example, known diffusers typically diffuse the air flow as the air flow travels along a generally
longitudinal axis 90 of the gas turbine system. However, the air flow exiting the compressor section generally has an “exit swirl” component, meaning that the air flow is traveling in a generally rotational direction, with tangential and radial flow components, along with traveling in a generally longitudinal direction. To reduce this exit swirl before the air flow enters theaxial diffuser 19, a guide vane orguide vanes 28 are typically disposed upstream of theaxial diffuser 19 in the compressor section. Theguide vanes 28 are designed to reduce the exit swirl. However, significant air flow pressure drops are associated with the use ofguide vanes 28 to reduce the exit swirl, which results in losses in the performance and efficiency of the gas turbine system. Further, after the air flow exits a typicalaxial diffuser 19, the air flow must change direction multiple times as it flows to the combustor section, as shown inFIG. 2 . Further significant air flow pressure drops are associated with each change in direction, thus resulting in further losses in the performance and efficiency of the gas turbine system. - Thus, a diffuser that reduces air flow pressure drops would be desired in the art. Additionally, a diffuser that utilizes the exit swirl associated with the air flow to guide the air flow to the combustor section would be advantageous. Further, a diffuser that eliminates the need for guide vanes in the compressor section would be desired.
- Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.
- In one embodiment, a diffuser for a gas turbine system having a longitudinal axis is disclosed. The diffuser includes a plurality of diffuser ducts. Each of the plurality of diffuser ducts is disposed annularly about the longitudinal axis and has an inlet, an outlet, and a passage extending between the inlet and the outlet. The outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct. Each of the plurality of diffuser ducts is configured to flow a gas flow therethrough, reducing the gas flow velocity.
- These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.
- A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:
-
FIG. 1 is a schematic view of a gas turbine system of the present disclosure; -
FIG. 2 is a cross-sectional view of a known gas turbine system; -
FIG. 3 is an exploded perspective view of one embodiment of a diffuser of the present disclosure; -
FIG. 4 is a perspective view of one embodiment of a diffuser duct of the present disclosure; -
FIG. 5 is a front view of one embodiment of a diffuser of the present disclosure; and -
FIG. 6 is a front view of another embodiment of a diffuser of the present disclosure. - Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.
-
FIG. 1 is a schematic diagram of agas turbine system 10. Thesystem 10 may include acompressor section 12, acombustor section 14, and aturbine section 16. Further, thesystem 10 may include a plurality ofcompressor sections 12,combustor sections 14, andturbine sections 16. Thecompressor section 12 andturbine section 16 may be coupled by ashaft 18. Theshaft 18 may be a single shaft or a plurality of shaft segments coupled together to formshaft 18. Thegas turbine system 10 may have a centrallongitudinal axis 90. For example, theshaft 18 may be disposed longitudinally along theaxis 90. - The
compressor section 12 may compress agas flow 80 as thegas flow 80 flows through thecompressor section 12. Thegas flow 80 may be, for example, air or any other suitable gas. Thecompressor section 12 may then flow thegas flow 80 to thecombustor section 14, which may be configured to accept thegas flow 80, as discussed below. - As the
gas flow 80 flows through thecompressor section 12 after being compressed, it may flow in a generally longitudinal direction with respect to thelongitudinal axis 90. However, thegas flow 80 may generally further include other flow components. For example, thegas flow 80 after being compressed may have flow components known collectively in the art as an “exit swirl.” Thus, thegas flow 80 may flow in a generally tangential direction, and may further flow in a generally radial direction. - In various embodiments, the
compressor section 12 may include at least oneguide vane 28. Theguide vane 28 may reduce the exit swirl, thus reducing the tangential and radial flow components of thegas flow 80. In exemplary embodiments of the present disclosure, however, thecompressor section 12 may be free fromguide vanes 28. - As shown in
FIGS. 3 through 6 , thecompressor section 12 may include adiffuser 20. Thediffuser 20 may be configured to reduce the velocity of thegas flow 80, as discussed below. Thediffuser 20 may further generally flow thegas flow 80 to thecombustor section 14. For example, after being compressed in thecompressor section 12,gas flow 80 may flow through thediffuser 20 and be provided to thecombustor section 14. For example, in one embodiment, thegas flow 80 may exit thediffuser 20 into aplenum 22. Thegas flow 80 may then be provided from theplenum 22 to thecombustor section 14. Alternatively, thegas flow 80 may exit thediffuser 20 directly into thecombustor section 14. For example, thecombustor section 14 may include a plurality ofcombustor cans 24. Further, in one embodiment as discussed below, thediffuser 20 may comprise a plurality ofdiffuser ducts 30. Each of thediffuser ducts 30 may be coupled with acombustor can 24. Thecombustor cans 24 may be configured to acceptgas flow 80 from one of the plurality ofdiffuser ducts 30. For example, each of thecombustor cans 24 may be fluidly connected to one of thediffuser ducts 30, such thatgas flow 80 exiting thediffuser ducts 30 immediately enters thecombustor cans 24, and thus thecombustor section 14. - As mentioned above, the
diffuser 20 of the present disclosure includes a plurality ofdiffuser ducts 30. As shown inFIGS. 3 through 6 , each of the plurality ofdiffuser ducts 30 may have aninlet 32, anoutlet 36, and a passage extending between theinlet 32 and theoutlet 36. Thediffuser ducts 30 may be configured to flow agas flow 80 therethrough, reducing thegas flow 80 velocity. For example, theinlet 32 of each of the plurality ofdiffuser ducts 30 may have a cross-sectional area that is generally smaller than the cross-sectional area of theoutlet 36 of therespective diffuser duct 30. Theinlets 32 andoutlets 36 may have generally circular or oval cross-sections, rectangular cross-sections, triangular cross-sections, or any other suitable polygonal cross-sections. Further, it should be understood that theinlet 32 andoutlet 34 of arespective diffuser duct 30 need not have similarly shaped cross-sections. For example, in one embodiment, theinlet 32 may have a generally rectangular cross-section, while theoutlet 36 may have a generally circular cross-section. - Further, the
passage 34 may be generally tapered between theinlet 32 and theoutlet 36. For example, in an exemplary embodiment, thepassage 34 may be generally conically shaped. Alternatively, however, thepassage 34 may have a generally rectangular cross-section, triangular cross-section, or any other suitable polygonal cross-section. It should be understood that the cross-sectional shape of thepassage 34 may change throughout thepassage 34 as thepassage 34 tapers from the relativelysmaller inlet 32 to the relativelylarger outlet 36. - The
diffuser ducts 30 may be disposed in an annular array about thelongitudinal axis 90. Thus, asgas flow 80 flows in a generally longitudinal direction through thecompressor section 12 and into thediffuser 20 after being compressed, thegas flow 80 may flow through theinlets 32 into the annular array ofdiffuser ducts 30. - The
outlet 36 of each of the plurality ofdiffuser ducts 30 may be offset from theinlet 32 of therespective diffuser duct 30. The term “offset”, as used herein, means spaced from along the identified coordinate direction. For example, theoutlet 36 of each of the plurality ofdiffuser ducts 30 may be tangentially offset from theinlet 32 of therespective diffuser duct 30, such as offset along atangential axis 92. Because theoutlet 36 of each of the plurality ofdiffuser ducts 30 is tangentially offset from theinlet 32 of therespective diffuser duct 30, thediffuser ducts 30 may advantageously utilize the tangential component of thegas flow 80 exit swirl to flow thegas flow 80 through thediffuser duets 30. In exemplary embodiments, this utilization of thetangential gas flow 80 component may eliminate the need forguide vanes 28 in thecompressor section 12. Further, the utilization of thetangential gas flow 80 component may preventgas flow 80 pressure losses due to flow direction changes in typical prior art gas turbine systems as thegas flow 80 flows from thecompressor section 12 through thediffuser 20 to thecombustor section 14. - Additionally, in some exemplary embodiments, the
outlet 36 of each of the plurality ofdiffuser ducts 30 may be longitudinally offset from theinlet 32 of therespective diffuser duct 30, such as offset along thelongitudinal axis 90. Because theoutlet 36 of each of the plurality ofdiffuser ducts 30 is longitudinally offset from theinlet 32 of therespective diffuser duct 30, thediffuser ducts 30 may advantageously utilize the longitudinal component of thegas flow 80 to flow thegas flow 80 through thediffuser ducts 30. - Further, in some exemplary embodiments, the
outlet 36 of each of the plurality ofdiffuser ducts 30 may be radially offset from theinlet 32 of therespective diffuser duct 30, such as offset along aradial axis 94. Because theoutlet 36 of each of the plurality ofdiffuser ducts 30 is radially offset from theinlet 32 of therespective diffuser duct 30, thediffuser ducts 30 may advantageously utilize the radial component of thegas flow 80 exit swirl to flow thegas flow 80 through thediffuser ducts 30. - It should be understood that the
tangential axis 92 and theradial axis 94 are defined individually for eachdiffuser duct 30 with respect to the circumference defined by thediffuser 20 anddiffuser ducts 30, as shown inFIGS. 5 and 6 , and that theaxes diffuser duct 30 about the circumference of thediffuser 20 based on the number ofdiffuser ducts 30 disposed in an annular array about thelongitudinal axis 90 of thediffuser 20. - Each of the
passages 34 may include afirst guide portion 40, as shown inFIG. 4 . In exemplary embodiments, thefirst guide portion 40 may be disposed adjacent theinlet 32 of therespective diffuser duct 30. Alternatively, however, thefirst guide portion 40 may be any portion of thepassage 34 of thediffuser duct 30. Thefirst guide portion 40 may be that portion of thepassage 34 that redirects the general direction ofgas flow 80 within adiffuser duct 30. For example, thefirst guide portions 40 may be configured to guide thegas flow 80 from a generally longitudinal flow direction to a generally tangential flow direction. Alternatively, thefirst guide portions 40 may be configured to guide thegas flow 80 from a generally longitudinal flow direction to a generally radial flow direction, a generally tangential and radial flow direction, a generally tangential and longitudinal flow direction, or to a generally tangential, radial, and longitudinal flow direction. It should be understood thatgas flow 80 in any general direction, such as in a generally longitudinal direction, may have other flow components, such as radial and tangential flow components, and is not limited to flow strictly in the referenced direction. - After
gas flow 80 passes through thefirst guide portion 40 of thepassage 34 of adiffuser duct 30, thegas flow 80 may continue to flow through thepassage 34 towards theoutlet 36. In certain exemplary embodiments, thepassages 34 may extend in a generally linear manner downstream of theguide portion 40 with respect to thegas flow 80, as shown inFIG. 6 . Thus, thegas flow 80, after passing through thefirst guide portion 40 of thepassage 34, may continue through thepassage 34 in a generally linear manner. In alternative exemplary embodiments, thepassages 34 may extend in a generally curvilinear manner downstream of theguide portion 40 with respect to thegas flow 80, as shown inFIGS. 3 through 5 . Thus, thegas flow 80, after passing through thefirst guide portion 40 of thepassage 34, may continue through thepassage 34 in a generally curvilinear manner. - Each of the
passages 34 may further include asecond guide portion 42. In exemplary embodiments, thesecond guide portion 42 may be disposed adjacent theoutlet 36 of therespective diffuser duct 30. Alternatively, however, thesecond guide portion 42 may be any portion of thepassage 34 of thediffuser duct 30. Thesecond guide portion 42 may be another portion of thepassage 34 that further redirects the general direction ofgas flow 80 within adiffuser duct 30. For example, thesecond guide portions 42 may be configured to guide thegas flow 80 from a generally tangential flow direction to a generally longitudinal flow direction. Alternatively, thesecond guide portions 42 may be configured to guide thegas flow 80 from a generally radial flow direction, a generally tangential and radial flow direction, a generally tangential and longitudinal flow direction, or a generally tangential, radial, and longitudinal flow direction to a generally longitudinal flow direction. It should be understood thatgas flow 80 in any general direction, such as in a generally longitudinal direction, may have other flow components, such as radial and tangential flow components, and is not limited to flow strictly in the referenced direction. - It should be understood that before
gas flow 80 passes through thesecond guide portion 42 of thepassage 34 of adiffuser duct 30, thegas flow 80 may flow through thepassage 34 towards theguide portion 42 and theoutlet 36. In certain exemplary embodiments, thepassages 34 may extend in a generally linear manner upstream of thesecond guide portion 42 with respect to thegas flow 80, as shown inFIG. 6 . Thus, thegas flow 80, before passing through thesecond guide portion 42 of thepassage 34, may travel through thepassage 34 in a generally linear manner. In alternative exemplary embodiments, thepassages 34 may extend in a generally curvilinear manner upstream of thesecond guide portion 42 with respect to thegas flow 80, as shown inFIGS. 3 through 5 . Thus, thegas flow 80, before passing through thesecond guide portion 42 of thepassage 34, may travel through thepassage 34 in a generally curvilinear manner. - After the
gas flow 80 flows through theoutlet 36 of adiffuser duct 30 of the present disclosure, thegas flow 80 may exit thediffuser 20. In some exemplary embodiments, thegas flow 80 may exit thediffuser 20 flowing in a generally tangential direction. It should be understood, however, that thegas flow 80 may have radial and longitudinal flow components, and is not limited to flow in a strictly tangential direction. Alternatively, thegas flow 80 may exit thediffuser 20 flowing in a generally longitudinal direction. It should be understood, however, that thegas flow 80 may have tangential and radial flow components, and is not limited to flow in a strictly longitudinal direction. Further, thegas flow 80 may exit thediffuser 20 flowing in a generally radial direction. It should be understood, however, that thegas flow 80 may have tangential and longitudinal flow components, and is not limited to flow in a strictly radial direction. - As discussed above, after the
gas flow 80 exits thediffuser 20 and thecompressor section 12, thegas flow 80 may enter aplenum 22, or may directly enter thecombustor section 14. For example, each of thediffuser ducts 30 may be coupled to acombustor can 24, and thegas flow 80 exiting eachdiffuser duct 30 may enter the combustor can 24 coupled with thediffuser duct 30. Thus, in exemplary embodiments, thediffuser 20 may include a number ofdiffuser ducts 20 equal to the number ofcombustor cans 24 in thecombustor 14. For example, thediffuser 20, in various embodiments, may include 8, 12, or 16diffuser ducts 30, or any other suitable number ofdiffuser ducts 30. - This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. 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 include 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.
Claims (20)
1. A diffuser for a gas turbine system having a longitudinal axis, the diffuser comprising:
a plurality of diffuser ducts, each of the plurality of diffuser ducts disposed annularly about the longitudinal axis and having an inlet, an outlet, and a passage extending between the inlet and the outlet,
wherein the outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct,
and wherein each of the plurality of diffuser ducts is configured to flow a gas flow therethrough, reducing the gas flow velocity.
2. The diffuser of claim 1 , wherein the outlet of each of the plurality of diffuser ducts is longitudinally offset from the inlet of the respective diffuser duct.
3. The diffuser of claim 1 , wherein the outlet of each of the plurality of diffuser ducts is radially offset from the inlet of the respective diffuser duct.
4. The diffuser of claim 1 , wherein gas flow exits the diffuser flowing in a generally tangential direction.
5. The diffuser of claim 1 , wherein gas flow exits the diffuser flowing in a generally longitudinal direction.
6. The diffuser of claim 1 , wherein each of the passages includes a guide portion disposed adjacent the inlet of the respective diffuser duct, the guide portions configured to guide the gas flow from a generally longitudinal flow direction to a generally tangential flow direction.
7. The diffuser of claim 6 , wherein the guide portions are further configured to guide the gas flow to a generally radial flow direction.
8. The diffuser of claim 6 , wherein each of the passages extends in a generally linear manner downstream of the guide portion with respect to the gas flow.
9. The diffuser of claim 6 , wherein each of the passages extends in a generally curvilinear manner downstream of the guide portion with respect to the gas flow.
10. The diffuser of claim 1 , wherein each of the passages includes a guide portion disposed adjacent the outlet of the respective diffuser duct, the guide portions configured to guide the gas flow from a generally tangential flow direction to a generally longitudinal flow direction.
11. The diffuser of claim 10 , wherein the guide portions are further configured to guide the gas flow from a generally radial flow direction.
12. The diffuser of claim 10 , wherein each of the passages extends in a generally linear manner upstream of the guide portion with respect to the gas flow.
13. The diffuser of claim 10 , wherein each of the passages extends in a generally curvilinear manner upstream of the guide portion with respect to the gas flow.
14. The diffuser of claim 1 , wherein each of the passages is generally conically shaped.
15. A gas turbine system having a longitudinal axis, the gas turbine system comprising:
a compressor section for compressing a gas flow;
a diffuser configured to reduce the velocity of the gas flow, the diffuser comprising a plurality of diffuser ducts, each of the plurality of diffuser ducts disposed annularly about the longitudinal axis and having an inlet, an outlet, and a passage extending between the inlet and the outlet, wherein the outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct, and wherein each of the plurality of diffuser ducts is configured to flow the gas flow therethrough; and
a combustor section configured to accept the gas flow from the diffuser.
16. The gas turbine system of claim 15 , wherein the compressor section is free from guide vanes.
17. The gas turbine system of claim 15 , the combustor section comprising a plurality of combustor cans, each of the combustor cans configured to accept the gas flow from one of the plurality of diffuser ducts.
18. The gas turbine system of claim 15 , wherein the outlet of each of the plurality of diffuser ducts is longitudinally offset from the inlet of the respective diffuser duct.
19. The gas turbine system of claim 15 , wherein the outlet of each of the plurality of diffuser ducts is radially offset from the inlet of the respective diffuser duct.
20. The gas turbine system of claim 15 , wherein each of the passages is generally conically shaped.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/774,262 US20110271654A1 (en) | 2010-05-05 | 2010-05-05 | Diffuser for gas turbine system |
JP2011094586A JP2011236897A (en) | 2010-05-05 | 2011-04-21 | Diffuser for gas turbine system |
EP11164824.2A EP2385219A3 (en) | 2010-05-05 | 2011-05-04 | Diffuser for gas turbine system between compressor exit and combustor inlet |
CN2011101251499A CN102235387A (en) | 2010-05-05 | 2011-05-05 | Diffuser for gas turbine system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/774,262 US20110271654A1 (en) | 2010-05-05 | 2010-05-05 | Diffuser for gas turbine system |
Publications (1)
Publication Number | Publication Date |
---|---|
US20110271654A1 true US20110271654A1 (en) | 2011-11-10 |
Family
ID=44170533
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/774,262 Abandoned US20110271654A1 (en) | 2010-05-05 | 2010-05-05 | Diffuser for gas turbine system |
Country Status (4)
Country | Link |
---|---|
US (1) | US20110271654A1 (en) |
EP (1) | EP2385219A3 (en) |
JP (1) | JP2011236897A (en) |
CN (1) | CN102235387A (en) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130224009A1 (en) * | 2012-02-29 | 2013-08-29 | David A. Little | Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section |
US20130224007A1 (en) * | 2012-02-29 | 2013-08-29 | Jose L. Rodriguez | Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section |
US9528392B2 (en) | 2013-05-10 | 2016-12-27 | General Electric Company | System for supporting a turbine nozzle |
US9777746B2 (en) | 2013-09-03 | 2017-10-03 | Dresser-Rand Company | Motor cooling system manifold |
US20190170353A1 (en) * | 2016-04-25 | 2019-06-06 | Mitsubishi Heavy Industries, Ltd. | Compressor diffuser and gas turbine |
US20190323519A1 (en) * | 2018-04-18 | 2019-10-24 | Mitsubishi Heavy Industries, Ltd. | Compressor diffuser and gas turbine |
US10550853B2 (en) | 2015-12-25 | 2020-02-04 | Kawasaki Jukogyo Kabushiki Kaisha | Gas turbine engine |
US20200049161A1 (en) * | 2018-08-10 | 2020-02-13 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes varying in natural vibration frequencies |
US11098650B2 (en) | 2018-08-10 | 2021-08-24 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes having aero-dampers |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111622985A (en) * | 2020-06-19 | 2020-09-04 | 上海尚实能源科技有限公司 | Diffuser integrating diffusion and rectification |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2475911A (en) * | 1944-03-16 | 1949-07-12 | Power Jets Res & Dev Ltd | Combustion apparatus |
US2582809A (en) * | 1944-12-30 | 1952-01-15 | Power Jets Res & Dev Ltd | Air and fuel regulating means in internal-combustion turbine power plants |
US4527386A (en) * | 1983-02-28 | 1985-07-09 | United Technologies Corporation | Diffuser for gas turbine engine |
US20100031663A1 (en) * | 2007-08-13 | 2010-02-11 | Snecma | Turbomachine with a diffuser |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3333762A (en) * | 1966-11-16 | 1967-08-01 | United Aircraft Canada | Diffuser for centrifugal compressor |
US3489340A (en) * | 1968-04-16 | 1970-01-13 | Garrett Corp | Centrifugal compressor |
DE2436458A1 (en) * | 1973-08-17 | 1975-02-20 | Int Harvester Co | CENTRIFUGAL COMPRESSORS |
US5131142A (en) * | 1990-10-30 | 1992-07-21 | Carrier Corporation | Method of making pipe diffuser structure |
US6123506A (en) * | 1999-01-20 | 2000-09-26 | Pratt & Whitney Canada Corp. | Diffuser pipe assembly |
US7156618B2 (en) * | 2004-11-17 | 2007-01-02 | Pratt & Whitney Canada Corp. | Low cost diffuser assembly for gas turbine engine |
US8038392B2 (en) * | 2007-07-18 | 2011-10-18 | Honda Motor Co., Ltd. | Axial diffuser for a centrifugal compressor |
-
2010
- 2010-05-05 US US12/774,262 patent/US20110271654A1/en not_active Abandoned
-
2011
- 2011-04-21 JP JP2011094586A patent/JP2011236897A/en not_active Withdrawn
- 2011-05-04 EP EP11164824.2A patent/EP2385219A3/en not_active Withdrawn
- 2011-05-05 CN CN2011101251499A patent/CN102235387A/en active Pending
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2475911A (en) * | 1944-03-16 | 1949-07-12 | Power Jets Res & Dev Ltd | Combustion apparatus |
US2582809A (en) * | 1944-12-30 | 1952-01-15 | Power Jets Res & Dev Ltd | Air and fuel regulating means in internal-combustion turbine power plants |
US4527386A (en) * | 1983-02-28 | 1985-07-09 | United Technologies Corporation | Diffuser for gas turbine engine |
US20100031663A1 (en) * | 2007-08-13 | 2010-02-11 | Snecma | Turbomachine with a diffuser |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130224007A1 (en) * | 2012-02-29 | 2013-08-29 | Jose L. Rodriguez | Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section |
US9476355B2 (en) * | 2012-02-29 | 2016-10-25 | Siemens Energy, Inc. | Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section |
US10012098B2 (en) * | 2012-02-29 | 2018-07-03 | Siemens Energy, Inc. | Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section |
US20130224009A1 (en) * | 2012-02-29 | 2013-08-29 | David A. Little | Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section |
US9528392B2 (en) | 2013-05-10 | 2016-12-27 | General Electric Company | System for supporting a turbine nozzle |
US9777746B2 (en) | 2013-09-03 | 2017-10-03 | Dresser-Rand Company | Motor cooling system manifold |
US10550853B2 (en) | 2015-12-25 | 2020-02-04 | Kawasaki Jukogyo Kabushiki Kaisha | Gas turbine engine |
US20190170353A1 (en) * | 2016-04-25 | 2019-06-06 | Mitsubishi Heavy Industries, Ltd. | Compressor diffuser and gas turbine |
US11060726B2 (en) * | 2016-04-25 | 2021-07-13 | Mitsubishi Heavy Industries, Ltd. | Compressor diffuser and gas turbine |
US20190323519A1 (en) * | 2018-04-18 | 2019-10-24 | Mitsubishi Heavy Industries, Ltd. | Compressor diffuser and gas turbine |
US20200049161A1 (en) * | 2018-08-10 | 2020-02-13 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes varying in natural vibration frequencies |
US10823196B2 (en) * | 2018-08-10 | 2020-11-03 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes varying in natural vibration frequencies |
US11098650B2 (en) | 2018-08-10 | 2021-08-24 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes having aero-dampers |
Also Published As
Publication number | Publication date |
---|---|
CN102235387A (en) | 2011-11-09 |
EP2385219A2 (en) | 2011-11-09 |
JP2011236897A (en) | 2011-11-24 |
EP2385219A3 (en) | 2013-06-05 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20110271654A1 (en) | Diffuser for gas turbine system | |
CN1214191C (en) | Dewwirler system for centrifugal compressor | |
US8047777B2 (en) | Turbomachine diffuser | |
US8109720B2 (en) | Exhaust plenum for a turbine engine | |
US8398359B2 (en) | Exhaust diffuser | |
EP1788310A3 (en) | System for Coupling Flow from a Centrifugal Compressor to an Axial Combustor for Gas Turbines | |
US11859543B2 (en) | Diffuser pipe with exit flare | |
EP3832144A1 (en) | Diffuser pipe with radially-outward exit | |
US10550729B2 (en) | Asymmetric gas turbine exhaust diffuser | |
US11143201B2 (en) | Impeller tip cavity | |
US8650852B2 (en) | Support assembly for transition duct in turbine system | |
US10781705B2 (en) | Inter-compressor flow divider profiling | |
CN107435656A (en) | Vortex flow spoiler on propeller | |
US11378005B1 (en) | Compressor diffuser and diffuser pipes therefor | |
US8448450B2 (en) | Support assembly for transition duct in turbine system | |
US20200318649A1 (en) | Diffuser pipe with asymmetry | |
US20130336783A1 (en) | Diffuser for turbomachines |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SIDEN, GUNNAR LEIF;REEL/FRAME:024338/0992 Effective date: 20100504 |
|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SIDEN, GUNNAR LEIF;REEL/FRAME:026121/0142 Effective date: 20110413 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |