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CN-122015132-A - Hydrogen injection for enhanced combustion stability in gas turbine systems

CN122015132ACN 122015132 ACN122015132 ACN 122015132ACN-122015132-A

Abstract

A hydrogen injection device (1) comprises an injector assembly comprising an external conduit (5) configured to feed a flow of a mixture of air and fuel to a combustion chamber (2 a) of a burner. At least one swirler (3) may be positioned in the outer conduit (5) to facilitate the swirl output of the air-fuel mixture (3 a) into the combustion chamber (2 a) such that the output fuel and air mixture includes a swirl output flow (12). The hydrogen gas stream may be passed through an internal hydrogen injection conduit (7) for output into the combustion chamber (2 a) for injection therein as a hydrogen gas jet.

Inventors

  • M.D. Dagostini
  • A. V. sane

Assignees

  • 气体产品与化学公司

Dates

Publication Date
20260512
Application Date
20220224
Priority Date
20220223

Claims (20)

  1. 1. A hydrogen injection apparatus for injecting hydrogen into a combustion chamber of a combustor of a gas turbine system, the hydrogen injection apparatus comprising: An outer conduit having an outlet in fluid communication with the combustion chamber, the outer conduit configured such that a mixture of fuel and air may be transferred into the combustion chamber via the outlet of the outer conduit, and An inner hydrogen injection conduit positioned adjacent to the outer conduit, the outer conduit positioned such that an outlet of the outer conduit surrounds an outer perimeter of an outlet of the inner hydrogen injection conduit in fluid communication with the combustion chamber, the inner hydrogen injection conduit configured such that at least one jet of hydrogen is sprayable into the combustion chamber via the outlet of the inner hydrogen injection conduit; Wherein the outlet of the internal hydrogen injection conduit is positioned to output the at least one jet of hydrogen towards a first wake zone within the combustion chamber, the first wake zone being downstream of the outlet of the internal hydrogen injection conduit and upstream of a location within the combustion chamber where a mixture of fuel and air output from the outlet of the external conduit passes through an exhaust zone of the outlet of the internal hydrogen injection conduit, wherein the internal hydrogen injection conduit is positioned and configured such that a secondary wake zone is formed by the at least one jet of hydrogen adjacent to or as it enters the first wake zone.
  2. 2. A hydrogen injection apparatus for injecting hydrogen into a combustion chamber of an operating combustor of a gas turbine system, the hydrogen injection apparatus comprising: An outer conduit having an outlet in fluid communication with the combustion chamber, the outer conduit configured such that a mixture of fuel and air may be transferred into the combustion chamber via the outlet of the outer conduit, and An inner hydrogen injection conduit positioned adjacent to the outer conduit, the outer conduit positioned such that an outlet of the outer conduit surrounds an outer perimeter of an outlet of the inner hydrogen injection conduit in fluid communication with the combustion chamber, the inner hydrogen injection conduit configured such that at least one jet of hydrogen is sprayable into the combustion chamber via the outlet of the inner hydrogen injection conduit; Wherein the outlet of the internal hydrogen injection conduit is positioned to output the at least one jet of hydrogen towards a first wake zone within the combustion chamber, the first wake zone being downstream of the outlet of the internal hydrogen injection conduit and upstream of a location within the combustion chamber where a mixture of fuel and air output from the outlet of the external conduit passes through an exhaust zone of the outlet of the internal hydrogen injection conduit, wherein the internal hydrogen injection conduit is positioned and configured such that a secondary wake zone is formed by the at least one jet of hydrogen adjacent to or as it enters the first wake zone.
  3. 3. The hydrogen injection apparatus of claim 2, wherein the outer conduit has at least one swirler to generate a swirling flow for a mixture of air and fuel to be output from an outlet of the outer conduit, and The secondary wake zone is located between the outlet of the inner hydrogen injection conduit and a location within the combustion chamber where a mixture of fuel and air output from the outlet of the outer conduit passes through the outlet of the inner hydrogen injection conduit when the fuel of the mixture is combusted in the combustion chamber.
  4. 4. The hydrogen injection apparatus of claim 2, wherein the outlet of the internal hydrogen injection conduit is a single orifice and the internal hydrogen injection conduit has at least one cavity upstream of the single orifice.
  5. 5. The hydrogen injection apparatus of claim 4, wherein the at least one cavity has a depth, a cavity length, and a cavity trailing edge distance, the cavity trailing edge distance being a distance of a downstream end of the cavity from an outlet of the internal hydrogen injection conduit; the cavity depth is greater than or equal to the radius of the orifice of the outlet of the internal hydrogen injection conduit and is also less than or equal to the diameter of the orifice of the outlet of the internal hydrogen injection conduit; The cavity length is a value such that the ratio of the length to the depth is between 1 and 4; the cavity trailing edge distance is a value such that a ratio of the cavity trailing edge distance to the diameter is no greater than 5.
  6. 6. The hydrogen injection apparatus of claim 2, wherein the outlet of the internal hydrogen injection conduit comprises a nozzle having at least one central orifice to form at least one central hydrogen jet to inject hydrogen into the combustion chamber and a plurality of external orifices to form a plurality of non-central hydrogen jets to inject hydrogen into the combustion chamber.
  7. 7. The hydrogen injection device of claim 6, wherein the external orifice is configured such that each of the non-central hydrogen jets outputs in a flow direction that flows at an angle to the flow direction of the at least one central hydrogen jet, the angle being greater than 0 ° and less than 90 ° or greater than 15 ° and less than 60 °.
  8. 8. The hydrogen injection device of claim 6, wherein the at least one central orifice is configured to form the at least one central hydrogen jet such that the at least one central hydrogen jet has a velocity of at least 100 m/s and the outer orifice is configured to form a non-central hydrogen jet having a velocity of at least 100 m/s.
  9. 9. The hydrogen injection apparatus of claim 2, wherein the outlet of the internal hydrogen injection conduit is a single orifice configured to inject the hydrogen gas as a jet of hydrogen gas having a velocity of at least 100 m/s.
  10. 10. A method of injecting hydrogen into a combustion chamber of a combustor of a gas turbine system, the method comprising: Outputting a mixture of fuel and air into the combustion chamber via an outlet of an external conduit in fluid communication with the combustion chamber; Injecting at least one jet of hydrogen into the combustion chamber via an outlet of an internal hydrogen injection conduit in fluid communication with the combustion chamber, and The outer conduit is positioned such that the outlet of the outer conduit surrounds the outer perimeter of the outlet of the inner hydrogen injection conduit; Wherein the at least one jet of hydrogen is injected towards a first wake zone within the combustion chamber downstream of the outlet of the internal hydrogen injection conduit and upstream of a location within the combustion chamber where a mixture of fuel and air output from the outlet of the external conduit passes through a discharge zone of the outlet of the internal hydrogen injection conduit within the combustion chamber.
  11. 11. The method of claim 10, wherein a secondary wake zone is formed by injecting the at least one jet of hydrogen gas toward the first wake zone.
  12. 12. The method of claim 11, comprising: Generating air vortex via at least one cyclone to generate cyclone flow for the mixture of air and fuel before outputting the mixture of air and fuel from the outlet of the external conduit, and Wherein the secondary wake zone is located between the outlet of the internal hydrogen injection conduit and a location within the combustion chamber where a mixture of fuel and air output from the outlet of the external conduit passes through the outlet of the internal hydrogen injection conduit when the fuel of the mixture is combusted in the combustion chamber.
  13. 13. The method of claim 10, wherein the outlet of the internal hydrogen injection conduit is a single orifice and the internal hydrogen injection conduit has at least one cavity upstream of the single orifice.
  14. 14. The method of claim 13, wherein the at least one cavity has a depth, a cavity length, and a cavity trailing edge distance, the cavity trailing edge distance being a distance of a downstream end of the cavity from an outlet of the internal hydrogen injection conduit; the cavity depth is greater than or equal to the radius of the orifice of the outlet of the internal hydrogen injection conduit and is also less than or equal to the diameter of the orifice of the outlet of the internal hydrogen injection conduit; The cavity length is a value such that the ratio of the length to the depth is between 1 and 4; the cavity trailing edge distance is a value such that a ratio of the cavity trailing edge distance to the diameter is no greater than 5.
  15. 15. The method of claim 10, wherein the at least one jet of hydrogen is at least one central jet of hydrogen and the outlet of the internal hydrogen injection conduit comprises a nozzle having at least one central orifice to form the at least one central jet of hydrogen to inject hydrogen into the combustion chamber and a plurality of external orifices to form a plurality of non-central jets of hydrogen to inject hydrogen into the combustion chamber, the method further comprising: the non-central hydrogen jet is injected into the combustion chamber via an external orifice of the nozzle.
  16. 16. The method of claim 15, wherein the external orifice is configured such that each of the non-central hydrogen jets outputs in a flow direction that flows at an angle to the flow direction of the at least one central hydrogen jet, the angle being greater than 0 ° and less than 90 ° or greater than 15 ° and less than 60 °.
  17. 17. The method of claim 15, wherein the at least one central hydrogen jet has a velocity of at least 100 m/s and each of the non-central hydrogen jets has a velocity of at least 100 m/s.
  18. 18. The method of claim 10, wherein the at least one jet of hydrogen has a velocity of at least 100 m/s.
  19. 19. The method of claim 10, comprising: generating air vortex via at least one cyclone to generate cyclone flow for the mixture of air and fuel before outputting the mixture of air and fuel from the outlet of the external conduit, and Delivering a swirling flow within the combustion chamber to a location where a mixture of fuel and air within the swirling flow passes through an exhaust region of an outlet of an internal hydrogen injection conduit within the combustion chamber; Wherein the at least one jet of hydrogen is injected into a secondary wake zone within the combustion chamber downstream of the outlet of the internal hydrogen injection conduit and upstream of a location within the combustion chamber where the mixture of fuel and air within the swirling flow passes through the discharge zone of the outlet of the internal hydrogen injection conduit, and Wherein the secondary wake zone is located between the outlet of the internal hydrogen injection conduit and a location within the combustion chamber where the mixture of fuel and air within the swirling flow passes through the outlet of the internal hydrogen injection conduit, the secondary wake zone having at least one second wake that interacts with at least one first wake within a first wake zone that is created by swirling flow of the mixture of air and fuel as the fuel is combusted within the combustion chamber.
  20. 20. The method of claim 19, wherein an activating gas from combustion of fuel in the at least one first wake communicates heat and active chemicals with the at least one second wake.

Description

Hydrogen injection for enhanced combustion stability in gas turbine systems The application is a divisional application of PCT patent application PCT/US2022/017674 (International application date is 2022, 02, 24, priority date is 2021, 02, 25, and China national application number 202280014871.1, entitled "Hydrogen injection for enhancing Combustion stability in gas turbine systems"), which enters China national stage at 14, 2023. Cross Reference to Related Applications The present application claims priority from U.S. patent application Ser. No. 17/678,134, filed on day 2022, month 02, and also claims priority from U.S. provisional patent application Ser. No. 63/153,620, filed on day 2021, month 02, and 25. Technical Field The present invention relates to gas turbines, injection devices for combustion chambers in gas turbine systems, operation of gas turbines, operation of injectors for combustion used in conjunction with gas turbine systems, apparatus utilizing one or more gas turbine systems, and methods of making and using the same. Background A gas turbine plant commonly used for industrial power generation is shown in fig. 1. It is understood from international publication No. WO 2019/222334 that such a device conventionally may comprise a cold section featuring a compressor followed by a hot section having a combustor section and a turbine. The cold section typically includes an air intake for feeding air to a multi-stage axial flow compressor that delivers high pressure air to the combustor section. The fuel may be mixed with an air stream and combusted in the combustion section to generate a high temperature, high pressure gas stream that is fed to the turbine. The turbine is located downstream of the combustor section and is configured to receive hot combustion gases from the combustor section and expand the flow of gases as the gases pass through the turbine, which causes the rotating blades of the turbine to rapidly rotate. Typically, the rotating blades of the turbine are attached to the shaft to rotate the shaft to perform a dual function (1) to help drive the compressor to draw more pressurized air into the combustor section, and (2) to quickly rotate the generator to generate electricity. The operating pressure ratio of the turbine, defined as the pressure of the air at the compressor outlet to the pressure of the air at the compressor inlet, is typically less than about 18:1. While the design of the combustor varies from manufacturer to manufacturer, size and application, many combustors, particularly multi-can (examples shown in FIG. 2) and annular can (examples shown in FIG. 3), perform combustion through a row of cylindrical tubes or "cans" disposed circumferentially about the turbine shaft. In a multi-can combustor, the air inlet of each can is mechanically coupled to a corresponding outlet port of the compressor. In contrast, annular can combustors are typically configured such that the inlet of each can is open to a common single ring connected to the compressor outlet. In either case, the products of combustion are discharged from each barrel through a transition duct and then distributed in the transition duct in an arc of about 360 ° into the first stage of the turbine. Each can combustor typically has a combustor chamber fed by one or more air-fuel nozzles disposed in an annular configuration around the circumference of the inlet plane of the can combustor. The air-fuel nozzle introduces a mixture of air and fuel into the combustor chamber. In many cases, an air-fuel pilot burner hearth is additionally provided along the burner axis. The air-fuel pilot furnace for enhanced combustion stability may be of a premixed design or a nozzle mixing (i.e., diffusion or non-premixed) design. The combination of premix nozzles and pilot hearths is commonly referred to as a hearth, and each can combustor generally includes its own hearth or group of hearths. Typically, the premix nozzles include fuel injectors that discharge fuel into corresponding air streams. Typically, the nozzles are arranged as annular nozzles comprising one or more fuel injectors arranged in an annular configuration surrounded by an air ring surrounding the central air-fuel pilot burner hearth. The furnace facilitates combustion of a mixture of air and fuel injected into a combustion chamber of a barrel of the combustion section to form hot gases that are fed to the turbine. Disclosure of Invention For environmental reasons, it is desirable to operate a gas turbine system such that its combustor or combustor section operates using lean combustion. The use of lean combustion may refer to the situation where there is an excess of air or oxygen for combustion relative to the fuel fed into the combustion chamber for combustion. Operating under lean combustion conditions may help reduce the formation of nitrogen oxides (NO x), which results in a more environmentally friendly exhaust gas output from the gas turbine system. Howe