WO2011149973A1 - Tangential combustor with vaneless turbine for use on gas turbine engines - Google Patents
Tangential combustor with vaneless turbine for use on gas turbine engines Download PDFInfo
- Publication number
- WO2011149973A1 WO2011149973A1 PCT/US2011/037786 US2011037786W WO2011149973A1 WO 2011149973 A1 WO2011149973 A1 WO 2011149973A1 US 2011037786 W US2011037786 W US 2011037786W WO 2011149973 A1 WO2011149973 A1 WO 2011149973A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- combustor
- fuel
- air
- nozzles
- flow
- Prior art date
Links
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
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- This invention relates to devices in gas turbine engines that contain the combustion of a fuel and air flow as well as devices that manipulate the hot gases' trajectory in such a way to take an ideal path entering the turbine stage.
- Such devices include but are not limited to fuel-air nozzles, combustor liners and casings, flow transition pieces, and guide vanes that are used in military and commercial aircraft, power generation, and other gas turbine related applications.
- the dilution holes serve two purposes depending on its axial position on the liner: a dilution hole closer to the fuel-air nozzles will cool the liner and aid in the mixing of the gases to enhance combustion as well as provide unburned air for combustion, second, a hole that is placed closer to the turbine will cool the hot gas flow and can be designed to manipulate the combustor outlet temperature profile.
- FIG. 3 is a side view of an annular combustor, with said corrugations, oriented such that the direction of flow is from left to right;
- FIG. 8B is a zoomed back view of the combustor highlighting the discharge openings for the hot combustion gases
- FIG. 10 is an isometric side view of an example annular combustor without corrugations with the proposed staged fuel and air injection;
- FIG. 12B is a close up view of the image from FIG. 12 A; and FIG. 13 is a two dimensional diagram showing a generic nozzle cross section layout of the fuel-air nozzles.
- FIG. 1 shows the general premise of the combustor and first stage turbine of a gas turbine engine.
- Hot, combusted gases 1 flow in the longitudinal direction where they exit the combustor threshold 8. From there, the gases are accelerated and guided by the first stage vane 2 from which the gases now have a resultant velocity 3 with a longitudinal component 4 and a circumferential component 5 and minimal radial component. This accelerated and turned gas flow then flows around the first stage turbine blades 6, where work is extracted and transferred to the turbine blades and the rotor connected thereto.
- FIG. 3 and 4 show the general design concept of the invention.
- the annular combustor is made up of essentially two concentric cylinders 14 & 15 forming an annular volume with the upstream end/opening of the two connected/enclosed with an annular face 13 called the front wall. These two cylinders may be of constant radius or have a variable radius that changes in the longitudinal and/or circumferential direction.
- Fuel- air nozzles are placed in a circumferential arrangement surrounding the outer liner where the flow generated has a strong tangential component in the said invention.
- a circular region 35 in the center of the nozzle may contain an axial s wirier where a rich fuel-air mixture passes through and/or a concentric pilot fuel-air nozzle.
- the key to the tangential fuel-air nozzles is the annular region 34 of the nozzle where air or lean premixed fuel-air mixture may enter with little to no swirl.
- the purpose of the annular inlet with low swirl is to ensure a substantial tangential inlet velocity into the combustor. This will increase the circumferential velocity component of the flow as it leaves the combustor into the turbine, allowing for a shorter 1 st stage turbine vane or corrugations.
- the operation of the invention is possible because the surfaces protruding into the combustor 16 & 17 volume create an obstruction in the hot gas flow that the combustor shell contains.
- the hot gas is therefore forced to follow the path of the corrugations as it would a row of stationary vanes.
- These various nozzles 24, 25 may share a common plane defined by the longitudinal direction and a point along the engine centerline and may be equally spaced circumferentially or have pattern to the spacing in this direction.
- the nozzles introduce a premixed fuel- air mixture 26 into the combustor volume created by the inner and outer shell 14, 15 and the front wall 32.
- the reactants that are injected by the fuel and air nozzles 24, 25 combust within this region and create a flow field 27 through the combustor that rotates about the engine centerline.
- the injection of the mixture near the front wall which may have a higher fuel/air ratio than the second set of nozzles in conjunction with the mixture that is injected downstream of the fuel nozzles 24, 25, creates the desired mixing and fuel-air staging effect that will create an optimal combustion environment that reduces NOx and CO emissions from the combustor.
- the hot combustion products then exit the combustor through an annular opening 23 as seen in FIG. 8A and 8B where it enters the first stage turbine of the gas turbine.
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201180026085.5A CN102985758B (en) | 2010-05-25 | 2011-05-24 | Tangential combustor with vaneless turbine for use on gas turbine engines |
JP2013512172A JP5842311B2 (en) | 2010-05-25 | 2011-05-24 | Tangential combustor with vaneless turbine for use in gas turbine engine |
RU2012153796A RU2619963C2 (en) | 2010-05-25 | 2011-05-24 | Tangential combustion chamber with vaneless turbine for gas turbine engine |
EP11787273.9A EP2577169B1 (en) | 2010-05-25 | 2011-05-24 | Tangential combustor with vaneless turbine for use on gas turbine engines |
HK13110816.6A HK1183511A1 (en) | 2010-05-25 | 2013-09-23 | Tangential combustor with vaneless turbine for use on gas turbine engines |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/786,882 | 2010-05-25 | ||
US12/786,882 US8904799B2 (en) | 2009-05-25 | 2010-05-25 | Tangential combustor with vaneless turbine for use on gas turbine engines |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2011149973A1 true WO2011149973A1 (en) | 2011-12-01 |
WO2011149973A8 WO2011149973A8 (en) | 2013-02-28 |
Family
ID=44504537
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2011/037786 WO2011149973A1 (en) | 2010-05-25 | 2011-05-24 | Tangential combustor with vaneless turbine for use on gas turbine engines |
Country Status (7)
Country | Link |
---|---|
US (1) | US8904799B2 (en) |
EP (1) | EP2577169B1 (en) |
JP (1) | JP5842311B2 (en) |
CN (1) | CN102985758B (en) |
HK (1) | HK1183511A1 (en) |
RU (1) | RU2619963C2 (en) |
WO (1) | WO2011149973A1 (en) |
Cited By (1)
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---|---|---|---|---|
EP2748533A4 (en) * | 2011-08-22 | 2015-03-04 | Majed Toqan | Tangential annular combustor with premixed fuel and air for use on gas turbine engines |
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JP5180807B2 (en) | 2008-12-24 | 2013-04-10 | 三菱重工業株式会社 | 1st-stage stationary blade cooling structure and gas turbine |
US9052114B1 (en) * | 2009-04-30 | 2015-06-09 | Majed Toqan | Tangential annular combustor with premixed fuel and air for use on gas turbine engines |
JP5479058B2 (en) * | 2009-12-07 | 2014-04-23 | 三菱重工業株式会社 | Communication structure between combustor and turbine section, and gas turbine |
RU2618785C2 (en) * | 2011-08-22 | 2017-05-11 | Маджед ТОКАН | Tangential and flameless annular combustion chamber for gas turbine engines |
KR101774093B1 (en) * | 2011-08-22 | 2017-09-12 | 마제드 토칸 | Can-annular combustor with staged and tangential fuel-air nozzles for use on gas turbine engines |
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US9291063B2 (en) * | 2012-02-29 | 2016-03-22 | Siemens Energy, Inc. | Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine |
US9228747B2 (en) * | 2013-03-12 | 2016-01-05 | Pratt & Whitney Canada Corp. | Combustor for gas turbine engine |
US11112115B2 (en) * | 2013-08-30 | 2021-09-07 | Raytheon Technologies Corporation | Contoured dilution passages for gas turbine engine combustor |
US10605459B2 (en) | 2016-03-25 | 2020-03-31 | General Electric Company | Integrated combustor nozzle for a segmented annular combustion system |
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- 2011-05-24 JP JP2013512172A patent/JP5842311B2/en active Active
- 2011-05-24 WO PCT/US2011/037786 patent/WO2011149973A1/en active Application Filing
- 2011-05-24 CN CN201180026085.5A patent/CN102985758B/en active Active
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EP2748533A4 (en) * | 2011-08-22 | 2015-03-04 | Majed Toqan | Tangential annular combustor with premixed fuel and air for use on gas turbine engines |
Also Published As
Publication number | Publication date |
---|---|
EP2577169B1 (en) | 2018-09-19 |
CN102985758A (en) | 2013-03-20 |
RU2012153796A (en) | 2014-06-27 |
US20110209482A1 (en) | 2011-09-01 |
JP5842311B2 (en) | 2016-01-13 |
WO2011149973A8 (en) | 2013-02-28 |
HK1183511A1 (en) | 2013-12-27 |
EP2577169A1 (en) | 2013-04-10 |
US8904799B2 (en) | 2014-12-09 |
RU2619963C2 (en) | 2017-05-22 |
CN102985758B (en) | 2015-04-01 |
EP2577169A4 (en) | 2017-04-12 |
JP2013527421A (en) | 2013-06-27 |
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