GB2134243A - Combustion equipment for a gas turbine engine - Google Patents
Combustion equipment for a gas turbine engine Download PDFInfo
- Publication number
- GB2134243A GB2134243A GB08302290A GB8302290A GB2134243A GB 2134243 A GB2134243 A GB 2134243A GB 08302290 A GB08302290 A GB 08302290A GB 8302290 A GB8302290 A GB 8302290A GB 2134243 A GB2134243 A GB 2134243A
- Authority
- GB
- United Kingdom
- Prior art keywords
- combustion chamber
- flared
- annular
- pot
- chamber
- 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.)
- Withdrawn
Links
Classifications
-
- 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
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
Abstract
A combustion chamber head (34) of a gas turbine engine annular combustion chamber (24) has a circumferential arrangement of flared pots (36) each of which has an aperture (37) at its upstream end and opens into the annular combustion chamber at its downstream end. A swirler assembly (42) and a fuel nozzle (58) are positioned coaxially within each aperture to supply primary air and fuel into the annular combustion chamber through the aperture. A flared member (50) is positioned coaxially within each pot downstream of the swirler assembly and is spaced from the pot to form an annular chamber (56). A swirler assembly (38) positioned in each pot supplies cooling air into the annular chamber to give a swirling flow of cooling air around the outer surface (52) of the flared member. The cooling air discharged from the downstream end of the annular chamber flows tangentially from the flared member to cool the combustion chamber head. The invention is intended to provide more efficient cooling of the flared member, and may be applied to other combustion chambers i.e. tubular combustion chambers. <IMAGE>
Description
SPECIFICATION
Combustion equipment for a gas turbine engine
The present invention relates to combustion equipment for a gas turbine engine and in particular it relates to cooling of a flared member positioned coaxially within a flared pot formed in the head of the combustion chamber.
The flared member positioned coaxially within a flared pot positioned in the head of a combustion chamber is subjected to relatively high temperatures generated by combustion of fuel within the combustion chamber. These high temperatures can cause the flared member to crack or flake and this has resulted in a requirement for cooling of the flared member to reduce the possibility of cracking or flaking.
In order to cool the flared member, cooling air has been directed radially onto the outer surface of the flared member to provide impingement cooling.
The present invention seeks to provide more effective cooling of the flared member.
Accordingly the present invention provides a combustion chamber for a gas turbine engine, the combustion chamber having a combustion chamber head at its upstream end, the combustion chamber head having at least one flared pot, the pot having an aperture at its upstream end and opening at the downstream end into the combustion chamber, a primary air swirling means being positioned coaxially within said aperture in the at least one flared pot to supply primary air into the combustion chamber through the aperture, a fuel burner being positioned coaxially within the primary air swirling means to supply fuel into the combustion chamber, a flared member being positioned coaxially within the flared pot downstream of the coaxial primary air swirling means and spaced from the flared pot to form an annular chamber, the annular chamber having a swirler assembly positioned in the flared pot for supplying cooling air into the annular chamber, the flared member extending into the combustion chamber at its downstream end, the cooling air supplied to the annular chamber swirling coaxially around and cooling the flared member as it flows in a downstream direction into the combustion chamber.
In a preferred embodiment an annular combustion chamber comprises inner and outer annular walls and an annular combustion chamber head which extends between the upstream ends of the inner and outer annular walls, the annular combustion chamber head has a circumferential arrangement of flared pots having an aperture at their upstream ends and opening at their downstream ends into the annular combustion chamber, a primary air swirling means being positioned coaxially within each said aperture to supply primary air into the annular combustion chamber through the aperture, a fuel burner being positioned coaxially within each primary air swirling means to supply fuel into the combustion chamber through the aperture, a flared member being positioned coaxially within each pot downstream of the coaxial primary air swirling means and spaced from pot to form an annular chamber, each annular chamber having a swirler assembly positioned in each pot for supplying cooling air into the annular chamber, each flared member extending into the annular combustion chamber at its downstream end, the cooling air supplied into the annular chamber swirling coaxially around and cooling the flared member as it flows in ia downstream direction into the annular combustion chamber.
In a further embodiment a tubular combustion chamber comprises a wall defining the tubular combustion chamber and a combustion chamber head at the upstream end of the wall, the combustion chamber head having a flared pot having an aperture at its upstream end and opening at the downstream end into the tubular combustion chamber, a primary air swirling means being positioned coaxially within the aperture in the flared pot to supply primary air into the tubular combustion chamber through the aperture, a fuel burner being positioned coaxially within the primary air swirling means to supply fuel into the tubular combustion chamber through the aperture, a flared member being positioned coaxially within the flared pot downstream of the coaxial primary air swirling means and spaced from the flared pot to form an annular chamber, the annular chamber having a swirler assembly positioned in the flared pot for supplying cooling air into the annular chamber, the flared member extending into the tubular combustion chamber at its downstream end, the cooling air supplied to the annular chamber swirling coaxially around and cooling the flared member as it flows in a downstream direction into the tubular combustion chamber.
Each flared member may have a flange at its downstream end to direct the cooling air radially, the cooling air flowing tangentially from the flange over the inner surface of the combustion chamber head.
Each flange may have a circumferential arrangement of tabs on its upstream surface to direct the cooling air to flow tangentially over the inner surface of the combustion chamber head.
Each flared member may converge towards the flared pot at its downstream end, and the area of each annular chamber at all sections perpendicular to the axis of the annular chamber may be equal.
The spacing between each flared member and the corresponding flared pot at all sec tions perpendicular to their axes may be equal.
The swirler assembly in the flared pot may comprise a number of equi-spaced swirl vanes or a number of equi-spaced slots arranged tangentially to the annular chamber.
The present invention will be more fully described with reference to the accompanying drawings in which:
Figure 1 shows a gas turbine engine with combustion equipment according to the present invention.
Figure 2 shows an enlarged section through the upstream end of the combustion equipment in Fig. 1.
Figure 3 shows an enlarged section through an alternative embodiment of the upstream end of the combustion equipment in Fig. 1.
Figure 4 shows an enlarged section of a further embodiment of the combustion equipment in Fig. 1.
Figure 5 shows a sectional view in the direction of arrows A-A in Fig. 2 and Figure 6 shows a section through the upstream end of a tubular combustion member comprising the present invention.
With reference to Fig. 1, which shows a typical arrangement of a bypass gas turbine engine 10 which comprises a fan 12 driven by a corresponding fan turbine 14, an intermediate pressure compressor 1 6 driven by a corresponding intermediate pressure turbine 18, a high pressure compressor 20 driven by a corresponding high pressure turbine 22 and an annular combustion chamber 24 which has a number of equi-spaced fuel burners 26.
The upstream end of the annular combustion chamber 24 is shown in more detail in
Fig. 2. The annular combustion chamber 24 comprises inner and outer annular walls 30 and 32 respectively and an annular combustion chamber head 34 which extends between the upstream ends of the inner and outer annular walls 30 and 32 respectively. The annular combustion chamber head 34 has a circumferential arrangement of flared pots 36, each of which has an aperture 37 at its upstream end and opens into the annular combustion chamber 24 at its downstream end. An annular member 40 is positioned at the upstream end of each pot 36 coaxially with the aperture 37, and a swirler assembly 42 is positioned coaxially within each aperture 37 and annular member 40.Each swirler assembly 42 comprises inner and outer coaxial circular walls 44 and 48 respectively which have a plurality of swirl vanes 46 extending therebetween to supply primary air into the annular combustion chamber 24 through the respective aperture 37. A plurality of fuel burners 26 supply fuel into the annular combustion chamber 24, each fuel burner 26 has a fuel nozzle 58 which is positioned coaxially within the inner circular wall 44 of the respective swirler assembly 42 and which supplies
fuel into the annular combustion chamber 24
through the aperture 37. A flared member 50
is positioned coaxially within each pot 36
downstream of the coaxial primary air swirler assembly 42 and is spaced from the pot 36 to
form an annular chamber 56.A swirler as
sembly 38 is positioned in each pot 36 to
supply cooling air into the annular chamber
56 to cool outer surface 52 of the flared
member 50. Each flared member 50 extends
into the annular combustion chamber 24 at its
downstream end, and each flared member 50
has a radially extending flange 54 at its
downstream end. Each flared member is se
cured to the pot 36 at its upstream end.
In operation, fuel is injected into the annu
lar combustion chamber 24 from each fuel
injector 58 through the aperture 37 in the
corresponding pot 36 and through the corre
sponding flared member 50. Primary air from
the high pressure compressor 20 is supplied
into the annular combustion chamber 24
through the swirler assembly 42 in the aper
ture 37 in each pot 36 and the corresponding
flared member 50. The primary air is swirled
as it passes through the swirler assembly 42
and mixes with the fuel injected from the fuel
injector 58 before it is ignited and burnt in
the annular combustion chamber 24.
The flared member 50 becomes very hot
due to the high temperatures generated by
the combustion of the fuel, and this can lead
to cracking or flaking of the flared member
50. To reduce the possibility of cracking or
flaking of the flared member 50, cooling air is
supplied through swirler assembly 38 in the
pot 36 into the annular chamber 56 formed
between the flared member 50 and the pot
36. The cooling air swirls coaxially around the
outer surface 52 of the flared member 50 and
flows in a downstream direction into the annu
lar combustion chamber 24. The flow of swirl
ing cooling air around the outer surface 52 of
the flared member 50 convectively cools the
flared member, and gives more effective cool
ing than impingement cooling. When the
swirling cooling air reaches the downstream
end of the flared member it is deflected
radially by the flange 54 to flow over the
inner surface of the annular combustion
chamber head 34. The cooling air leaves the
flange 54 tangentially as shown by arrows B
in Fig. 5 because of its swirling motion and
attaches to the inner surface of the annular
combustion chamber head 34 to give even
film cooling. The flange 54 ensures that the
cooling air does not disturb the combusting
fuel and primary air mixture.
Fig. 3 shows an alternative embodiment of
the flared member 50 which is similar to the
embodiment shown in Figs. 2 and 5, but
which also has a circumferential arrangement
of tabs 60 on the upstream surface of the
flange 54. The swirling cooling air is deflected
radially by the flange 50 and then flows between the tabs 60 and is directed to flow in a tangential direction over the inner surface of the annular combustion chamber head 34 to give even film cooling.
Fig. 4 shows an alternative embodiment of the flared member 50 and pot 36 in which the flared member 50 converges towards the pot 36 at its downstream end. The annular chamber 56 can then be arranged so that the area for flow of cooling air at all sections perpendicular to the axis of the annular chamber are equal by selecting the appropriate amount of convergence between the flared member 50 and the flared pot 36. By having a constant flow area along the axial length of the annular chamber 56 diffusion of the cooling air within the annular chamber 56 is prevented.
The swirling assembly 38 may comprise a number of swirl vanes or a number of apertures in the flared pot 36 which are arranged to supply cooling air tangentially into the annular chamber 56.
The annular chamber 56 is arranged in
Figs. 2 and 3 so that the area for flow of cooling air in sections perpendicular to the axis of the annular chamber increases in a downstream direction to give diffusion of the cooling air within the annular chamber 56. In the particular examples the spacing between the flared pot 36 and flared member 50 remains constant through their axial lengths.
The present invention may equally well be applied to a tubular combustion chambers 66 as shown in Fig. 6, which comprises a wall 68 which defines the combustion chamber and a combustion chamber head 70. A flared pot 72 which has an aperture 86 at its upstream end which opens into the tubular combustion chamber 66 is positioned in the combustion chamber head 70 coaxial with the combustion chamber 66. An annular member 76 is positioned at the upstream end of the pot 72 coaxially with the aperture 86, and a swirler assembly 78 is positioned coaxially within the aperture 37 and annular member 76. The swirler assembly comprises inner and outer circular walls 80 and 84 respectively which have a plurality of swirl vanes 82 extending therebetween to supply primary air into the tubular combustion chamber 66 through the aperture 86.A fuel nozzle 58 of a fuel burner 26 is positioned coaxially within the inner circular wall 80 of the swirler assembly 78 and supplies fuel into the tubular combustion chamber 66 through the aperture 86. A flared member 88 is positioned coaxially within the flared pot 72 and is spaced from the pot 72 to form an annular chamber 94.
The flared member 88 extends into the tubular combustion chamber 66 at its downstream end and has a radially extending flange 92 at its downstream end. A swirler assembly 74 in the pot 72 supplies cooling air into the annular chamber 94, the cooling air swirls coaxially around the outer surface 90 of the flared member 88 to give effective cooling and also flows in a downstream direction. The cooling air leaves the downstream end of the flared member 88 and is deflected to flow radially by the flange 92 over the inner surface of the tubular combustion chamber head 70. The cooling air leaves the flange 92 tangentially because of its swirling motion.
Claims (11)
1. A combustion chamber for a gas turbine engine, the combustion chamber having a combustion chamber head at its upstream end, the combustion chamber head having at least one flared pot, the pot having an aperture at its upstream end and opening at the downstream end into the combustion chamber, a primary air swirling means being positioned coaxially within the aperture in the at least one flared pot to supply primary air into the combustion chamber through the aperture, a fuel burner being positioned coaxially within the primary air swirling means to supply fuel into the combustion chamber, a flared member being positioned coaxially within the flared pot downstream of the coaxial primary air swirling means and spaced from the flared pot to form an annular chamber, the annular chamber having a swirler assembly positioned in the flared pot for supplying cooling air into the annular chamber, the flared member extending into the combustion chamber at its downstream end, the cooling air supplied to the annular chamber swirling coaxially around and cooling the flared member as it flows in a downstream direction into the combustion chamber.
2. A combustion chamber as claimed in claim 1 in which the combustion chamber is an annular combustion chamber comprising inner and outer annular walls and an annular combustion chamber head extending between the upstream ends of the inner and outer annular walls, the annular combustion chamber head having a circumferential arrangement of flared pots having at their upstream ends an aperture and opening at their downstream end into the annular combustion chamber, a primary air swirling means being positioned coaxially within each said aperture to supply primary air into the annular combustion chamber through the aperture, a fuel burner being positioned coaxially within each primary air swirling means to supply fuel into the combustion chamber through the aperture, a flared member being positioned coaxially within each pot downstream of the coaxial primary air swirling means and spaced from the pot to form an annular chamber, each annular chamber having a swirler assembly positioned in each pot for supplying cooling air into the annular chamber, each flared member extending into the annular combus tion chamber at its downstream end, the cooling air supplied to the annular chamber swirling coaxially around and cooling the flared member as it flows in a downstream direction into the annular combustion chamber.
3. A combustion chamber as claimed in claim 1 in which the combustion chamber is a tubular combustion chamber comprising a wall defining the tubular combustion chamber, and a combustion chamber head at the upstream end of the wall, the combustion chamber head having a flared pot having an aperture at its upstream end and opening at the downstream end into the tubular combustion chamber, a primary air swirling means being positioned coaxially within the aperture in the flared pot to supply primary air into the tubular combustion chamber through the aperture, a fuel burner being positioned coaxially within the primary air swirling means to supply fuel into the tubular combustion chamber through the aperture, a flared member being positioned coaxially within the flared pot downstream of the coaxial primary air swirling means and spaced from the flared pot to form an annular chamber, the annular chamber having a swirler assembly positioned in the flared pot for supplying cooling air into the annular chamber, the flared member extending into the tubular combustion chamber at its downstream end, the cooling air supplied to the annular chamber swirling coaxially around and cooling the flared member as it flows in a downstream direction into the tubular combustion chamber.
4. A combustion chamber as claimed in any of claim 1 to 3 in which each flared member has a flange at its downstream end to direct the cooling air radially, the cooling air flowing tangentially from the flange over the inner surface of the combustion chamber head.
5. A combustion chamber as claimed in claim 4 in which each flange has a circumferential arrangement of tabs on its upstream surface to direct the cooling air to flow tangentially over the inner surface of the combustion chamber head.
6. A combustion chamber as claimed in any of claims 1 to 5 in which each flared member converges towards the flared pot at its downstream end.
7. A combustion chamber as claimed in claim 6 in which the area of each annular chamber at all sections perpendicular to its axis are equal.
8. A combustion chamber as claimed in any of claims 1 to 5 in which the spacing between each flared member and the corresponding flared pot at all sections perpendicular to their axes are equal.
9. A combustion chamber as claimed in any of the preceding claims in which the swirler assembly in the flared pot comprises a number of equi-spaced swirl vanes.
10. A combustion chamber as claimed in any of the preceding claims in which the swirler assembly in the flared pot comprises a number of equi-spaced slots arranged tangentially to the annular chamber.
11. A gas turbine combustion chamber constructed and arranged for use and operation substantially as herein described with reference to and as shown in Figs. 1, 2 and 5, Fig. 3, Fig. 4 or Fig. 6 of the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08302290A GB2134243A (en) | 1983-01-27 | 1983-01-27 | Combustion equipment for a gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08302290A GB2134243A (en) | 1983-01-27 | 1983-01-27 | Combustion equipment for a gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB2134243A true GB2134243A (en) | 1984-08-08 |
Family
ID=10537042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08302290A Withdrawn GB2134243A (en) | 1983-01-27 | 1983-01-27 | Combustion equipment for a gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2134243A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2585770A1 (en) * | 1985-08-02 | 1987-02-06 | Snecma | EXPANDED BOWL INJECTION DEVICE FOR TURBOMACHINE COMBUSTION CHAMBER |
| US4754600A (en) * | 1986-03-20 | 1988-07-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Axial-centripetal swirler injection apparatus |
| EP0469899A1 (en) * | 1990-08-02 | 1992-02-05 | General Electric Company | Combustor dome assembly |
| EP0550218A1 (en) * | 1991-12-30 | 1993-07-07 | General Electric Company | Gas turbine combustors |
| EP1253380A2 (en) * | 2001-04-27 | 2002-10-30 | General Electric Company | Methods and apparatus for cooling gas turbine engine combustors |
| US7032386B2 (en) | 2001-06-27 | 2006-04-25 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| WO2010136287A2 (en) * | 2009-05-27 | 2010-12-02 | Siemens Aktiengesellschaft | Burner, operating method and assembly method |
| CN102506446A (en) * | 2011-10-13 | 2012-06-20 | 中国科学院工程热物理研究所 | Fuel and air mixing device for low-pollution burning chamber of gas turbine |
| US10712008B2 (en) | 2016-10-13 | 2020-07-14 | Rolls-Royce Plc | Combustion chamber and a combustion chamber fuel injector seal |
| US11085643B2 (en) | 2018-02-12 | 2021-08-10 | Rolls-Royce Plc | Air swirler arrangement for a fuel injector of a combustion chamber |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB710353A (en) * | 1951-06-18 | 1954-06-09 | Rolls Royce | Improvements in or relating to combustion equipment for gas-turbine engines |
| GB715909A (en) * | 1952-02-01 | 1954-09-22 | Rolls Royce | Improvements in or relating to combustion equipment of gas-turbine engines |
| GB742657A (en) * | 1953-01-16 | 1955-12-30 | Rolls Royce | Improvements in or relating to hot-gas-conveying ducting |
| GB791753A (en) * | 1955-02-23 | 1958-03-12 | Bristol Aero Engines Ltd | Improvements in or relating to flame tubes for use in combustion systems of gas turbine engines |
| GB2020370A (en) * | 1978-03-04 | 1979-11-14 | Lucas Industries Ltd | Combustion assembly |
| GB2034874A (en) * | 1978-11-03 | 1980-06-11 | Gen Electric | Gas turbine engine combustor |
| GB2073398A (en) * | 1980-04-02 | 1981-10-14 | United Technologies Corp | Fuel nozzle guide and seal for a gas turbine engine |
-
1983
- 1983-01-27 GB GB08302290A patent/GB2134243A/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB710353A (en) * | 1951-06-18 | 1954-06-09 | Rolls Royce | Improvements in or relating to combustion equipment for gas-turbine engines |
| GB715909A (en) * | 1952-02-01 | 1954-09-22 | Rolls Royce | Improvements in or relating to combustion equipment of gas-turbine engines |
| GB742657A (en) * | 1953-01-16 | 1955-12-30 | Rolls Royce | Improvements in or relating to hot-gas-conveying ducting |
| GB791753A (en) * | 1955-02-23 | 1958-03-12 | Bristol Aero Engines Ltd | Improvements in or relating to flame tubes for use in combustion systems of gas turbine engines |
| GB2020370A (en) * | 1978-03-04 | 1979-11-14 | Lucas Industries Ltd | Combustion assembly |
| GB2034874A (en) * | 1978-11-03 | 1980-06-11 | Gen Electric | Gas turbine engine combustor |
| GB2073398A (en) * | 1980-04-02 | 1981-10-14 | United Technologies Corp | Fuel nozzle guide and seal for a gas turbine engine |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2585770A1 (en) * | 1985-08-02 | 1987-02-06 | Snecma | EXPANDED BOWL INJECTION DEVICE FOR TURBOMACHINE COMBUSTION CHAMBER |
| EP0214003A1 (en) * | 1985-08-02 | 1987-03-11 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Fuel injection nozzle with an enlarged screen for the combustion chamber of a gas turbine |
| US4766722A (en) * | 1985-08-02 | 1988-08-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Enlarged bowl member for a turbojet engine combustion chamber |
| US4754600A (en) * | 1986-03-20 | 1988-07-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Axial-centripetal swirler injection apparatus |
| EP0469899A1 (en) * | 1990-08-02 | 1992-02-05 | General Electric Company | Combustor dome assembly |
| US5117637A (en) * | 1990-08-02 | 1992-06-02 | General Electric Company | Combustor dome assembly |
| EP0550218A1 (en) * | 1991-12-30 | 1993-07-07 | General Electric Company | Gas turbine combustors |
| US5253478A (en) * | 1991-12-30 | 1993-10-19 | General Electric Company | Flame holding diverging centerbody cup construction for a dry low NOx combustor |
| EP1253380A2 (en) * | 2001-04-27 | 2002-10-30 | General Electric Company | Methods and apparatus for cooling gas turbine engine combustors |
| EP1253380A3 (en) * | 2001-04-27 | 2003-10-22 | General Electric Company | Methods and apparatus for cooling gas turbine engine combustors |
| US7032386B2 (en) | 2001-06-27 | 2006-04-25 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| WO2010136287A2 (en) * | 2009-05-27 | 2010-12-02 | Siemens Aktiengesellschaft | Burner, operating method and assembly method |
| WO2010136287A3 (en) * | 2009-05-27 | 2012-05-18 | Siemens Aktiengesellschaft | Burner, operating method and assembly method |
| CN102597632A (en) * | 2009-05-27 | 2012-07-18 | 西门子公司 | Burner, operating method and assembly method |
| RU2541482C2 (en) * | 2009-05-27 | 2015-02-20 | Сименс Акциенгезелльшафт | Burner and gas turbine with such burner |
| US9127842B2 (en) | 2009-05-27 | 2015-09-08 | Siemens Aktiengesellschaft | Burner, operating method and assembly method |
| CN102597632B (en) * | 2009-05-27 | 2016-08-24 | 西门子公司 | Burner, operational approach and assemble method |
| CN102506446A (en) * | 2011-10-13 | 2012-06-20 | 中国科学院工程热物理研究所 | Fuel and air mixing device for low-pollution burning chamber of gas turbine |
| CN102506446B (en) * | 2011-10-13 | 2013-10-09 | 中国科学院工程热物理研究所 | Fuel and air mixing device for low-pollution burning chamber of gas turbine |
| US10712008B2 (en) | 2016-10-13 | 2020-07-14 | Rolls-Royce Plc | Combustion chamber and a combustion chamber fuel injector seal |
| US11085643B2 (en) | 2018-02-12 | 2021-08-10 | Rolls-Royce Plc | Air swirler arrangement for a fuel injector of a combustion chamber |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |