GB2512642A - A combustion chamber - Google Patents
A combustion chamber Download PDFInfo
- Publication number
- GB2512642A GB2512642A GB201306124A GB201306124A GB2512642A GB 2512642 A GB2512642 A GB 2512642A GB 201306124 A GB201306124 A GB 201306124A GB 201306124 A GB201306124 A GB 201306124A GB 2512642 A GB2512642 A GB 2512642A
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- GB
- United Kingdom
- Prior art keywords
- dilution
- apertures
- triangular cross
- combustion chamber
- dilution apertures
- 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.)
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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
- F23R3/06—Arrangement of apertures along the flame tube
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A combustion chamber 15 has an annular wall 40 with two rows of dilution apertures 58, 60 spaced apart axially. In each row, dilution apertures are circumferentially spaced, and each aperture has a polygonal cross-sectional shape, e.g. a triangle. Apertures in adjacent rows are staggered circumferentially, and a corner 62A of each dilution aperture in one row is axially upstream of a corner 64A of each dilution aperture in the adjacent row. The axial distance taken up by the two rows of dilution apertures in the annular wall is reduced compared to the use of two rows of circular dilution apertures and enables a greater mass flow of dilution air through a shorter axial distance giving better quenching of the rich burn combustion process and a reduction in nitrous oxide emissions.
Description
A COMBUSTION CHAMBER
Field of the Invention
The present invention relates to a combustion chamber and in particular to a gas turbine engine combustion chamber.
Background to the Invention
Conventional gas turbine engine combustion chambers have a row of circumferentially spaced dilution apertures in each wall of the combustion chamber to supply dilution air into the combustion chamber.
US20090308077A1 discloses in a rich burn annular combustion chamber that the row of dilution apertures in an outer annular wall has dilution apertures with different diameters and the row of dilution apertures in an inner annular wall has dilution apertures with different diameters.
A problem with this arrangement is that beyond a certain limit no more dilution air can be supplied into the combustion chamber.
Therefore the present invention seeks to provide a novel combustion chamber which reduces or overcomes the above mentioned problem.
Statements of Invention
Accordingly the present invention provides a combustion chamber comprising at least one annular wall, the at least one annular wall having at least two rows of dilution apertures, each row of dilution apertures comprising a plurality of circumferentially spaced dilution apertures, each dilution aperture having a substantially polygonal cross-sectional shape, the dilution apertures in adjacent rows of dilution apertures being staggered circumferentially, and a corner of each polygonal cross-sectional shaped dilution aperture in one of the adjacent rows of dilution apertures being axially upstream of a corner of each polygonal cross-sectional shaped dilution aperture in the other of the adjacent rows of dilution apertures.
The dilution apertures may have triangular cross-sectional shape, a rhombus cross-sectional shape or a pentagonal cross-sectional shape.
The present invention also provides a combustion chamber comprising at least one annular wall, the at least one annular wall having at least two rows of dilution apertures, each row of dilution apertures comprising a plurality of circumferentially spaced dilution apertures, each dilution aperture having a substantially triangular cross-sectional shape, the dilution apertures in adjacent rows of dilution apertures being staggered circumferentially, and a corner of each triangular cross-sectional shaped dilution aperture in one of the adjacent rows of dilution apertures being axially upstream of a corner of each triangular cross-sectional shaped dilution aperture in the other of the adjacent rows of dilution apertures.
The rows of dilution apertures may be spaced apart axially.
One of the sides of each triangular cross-sectional shaped dilution aperture in one of the adjacent rows of dilution apertures may extend circumferentially. One of the sides of each triangular cross-sectional shaped dilution aperture in the other of the adjacent rows of dilution apertures may extend circumferentially.
The triangular cross-sectional shaped dilution apertures in the adjacent rows of dilution apertures may have identical shapes. The triangular cross-sectional shaped dilution apertures in the adjacent rows of dilution apertures may have identical cross-sectional areas.
The triangular cross-sectional shaped dilution apertures may be right angle triangles, equilateral triangles, isosceles triangles or scalene triangles.
The triangular cross-sectional shaped dilution apertures may have rounded corners.
The triangular cross-sectional shaped dilution apertures may be keyhole shaped.
The corner of each triangular cross-sectional shaped dilution aperture in one of the adjacent rows of dilution apertures may be arranged axially in the same plane as the sides of the triangular cross-sectional shaped dilution apertures in the other of the adjacent rows of triangular shaped dilution apertures. The corner of each triangular cross-sectional shaped dilution aperture in the other of the adjacent rows of dilution apertures may be arranged axially in the same plane as the sides of the triangular cross-sectional shaped dilution apertures in the one of the adjacent rows of triangular shaped dilution apertures.
Preferably the base of each triangular cross-sectional shaped dilution aperture in the adjacent rows of triangular cross-sectional shaped dilution apertures extends circumferentially and each triangular cross-sectional shaped dilution aperture in one of the rows of triangular cross-sectional shaped dilution apertures is positioned circumferentially between two adjacent triangular cross-sectional shaped dilution apertures in the other row of triangular cross-sectional shaped dilution apertures. Each side of each triangular cross-sectional shaped dilution aperture in one of the rows of triangular cross-sectional shaped dilution apertures may be parallel with one of the sides of one of the two adjacent triangular cross-sectional shaped dilution apertures in the adjacent row of triangular cross-sectional shaped dilution apertures.
The combustion chamber may be a gas turbine engine combustion chamber.
The combustion chamber may be a tubular combustion chamber or an annular combustion chamber.
The combustion chamber may have a radially inner annular wall and a radially outer annular wall. The radially inner annular wall and/or the radially outer annular wall may have at least two rows of dilution apertures.
Brief Description of the Drawings
The present invention will be more fully described by way of example with reference to the accompanying drawings, in which:-Figure 1 is partially cut away view of a turbofan gas turbine engine having a wall of a combustion chamber manufactured using a method according to the present invention.
Figure 2 is an enlarged cross-sectional view of a wall of a combustion chamber according to the present invention.
Figure 3 is a view in the direction of arrow Y in figure 2.
Figure 4 is an alternative view in the direction of arrow Yin figure 2.
Figure 5 is a further alternative view in the direction of arrow Y in figure 2.
Figure 6 is a further alternative view in the direction of arrow Y in figure 2.
Detailed Description
A turbofan gas turbine engine 10, as shown in figure 1, comprises in flow series an intake 11, a fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, an intermediate pressure turbine 17, a low pressure turbine 18 and an exhaust 19. The high pressure turbine 16 is arranged to drive the high pressure compressor 14 via a first shaft 26.
The intermediate pressure turbine 17 is arranged to drive the intermediate pressure compressor 13 via a second shaft 28 and the low pressure turbine 18 is arranged to drive the fan 12 via a third shalt 30. In operation air flows into the intake 11 and is compressed by the fan 12. A first portion of the air flows through, and is compressed by, the intermediate pressure compressor 13 and the high pressure compressor 14 and is supplied to the combustion chamber 15. Fuel is injected into the combustion chamber 15 and is burnt in the air to produce hot exhaust gases which flow through, and drive, the high pressure turbine 16, the intermediate pressure turbine 17 and the low pressure turbine 18. The hot exhaust gases leaving the low pressure turbine 18 flow through the exhaust 19 to provide propulsive thrust. A second portion of the air bypasses the main engine to provide propulsive thrust.
The combustion chamber 15, as shown more clearly in figure 2, is an annular combustion chamber and comprises a radially inner annular wall structure 40, a radially outer annular wall structure 42 and an upstream end wall structure 44. The radially inner annular wall structure 40 comprises a first annular wall 46 and a second annular wall 48. The radially outer annular wall structure 42 comprises a third annular wall 50 and a fourth annular wall 52. The second annular wall 48 is spaced radially from and is arranged radially around the first annular wall 46 and the first annular wall 46 supports the second annular wall 48. The fourth annular wall 52 is spaced radially from and is arranged radially within the third annular wall 50 and the third annular wall 50 supports the fourth annular wall 52. The upstream end of the first annular wall 46 is secured to the upstream end wall structure 44 and the upstream end of the third annular wall 50 is secured to the upstream end wall structure 44. The upstream end wall structure 44 has a plurality of circumferentially spaced apertures 54 and each aperture 54 has a respective one of a plurality of fuel injectors 56 located therein. The fuel injectors 56 are arranged to supply fuel into the annular combustion chamber 15 during operation of the gas turbine engine 10.
The radially inner annular wall structure 40 has at least two rows of dilution apertures 58 and 60 and the two rows of dilution apertures 58 and 60 are spaced apart axially along the radially inner annular wall 40, as shown more clearly in figures 2 and 3. The row of dilution apertures 60 is axially upstream of the row of dilution apertures 58. The rows of dilution apertures 58 and 60 extend through the first annular wall 46 and the second annular wall 48. Each row of dilution apertures 58 and 60 comprises a plurality of circumferentially spaced dilution apertures 62 and 64 respectively and each dilution aperture 62 and 64 has a substantially triangular cross-sectional shape. The dilution apertures 62 and 64 in the adjacent rows of dilution apertures 58 and 60 respectively are staggered circumferentially.
Each triangular cross-sectional shaped dilution aperture 62 has three corners 62A, 62B and 62C and three sides 620. 62E and 62F. Each triangular cross-sectional shaped dilution aperture 64 has three corners 64A, 64B and 64C and three sides 640, 64E and 64F. A corner 62A of each triangular cross-sectional shaped dilution aperture 62 in one of the adjacent rows of dilution apertures 58 is axially upstream of a corner 64A of each triangular cross-sectional shaped dilution aperture 64 in the other of the adjacent rows of dilution apertures 60. One of the sides, the base, 620 of each triangular cross-sectional shaped dilution aperture 62 in one of the adjacent rows of dilution apertures 58 extends circumferentially and one of the sides, the base, 640 of each triangular cross-sectional shaped dilution aperture 64 in the other of the adjacent rows of dilution apertures 60 extends circumferentially. Each side 62D extends between the corners 62B and 62C of the respective triangular cross-sectional shaped dilution aperture 62 and each side 640 extends between the corners 64B and 640 of the respective triangular cross-sectional shaped dilution aperture 64.
The triangular cross-sectional shaped dilution apertures 62 and 64 in the adjacent rows of dilution apertures 58 and 60 have identical shapes and the triangular cross-sectional shaped dilution apertures 62 and 64 in the adjacent rows of dilution apertures 58 and have identical cross-sectional areas. The triangular cross-sectional shaped dilution apertures 62 and 64 are equilateral triangles, but the triangular cross-sectional shaped dilution apertures may be right angle triangles, isosceles triangles or scalene triangles.
The triangular cross-sectional shaped dilution apertures 62 and 64 may have rounded corners to reduce stresses. The bases 620 of the triangular cross-sectional shaped dilution apertures 62 are parallel with the bases 640 of the triangular cross-sectional shaped dilution apertures 64, the sides 62E of the triangular cross-sectional shaped dilution apertures 62 are parallel with the sides 64E of the triangular cross-sectional shaped dilution apertures 64 and the sides 62F of the triangular cross-sectional shaped dilution apertures 62 are parallel with the sides 64F of the triangular cross-sectional shaped dilution apertures 64 so that there is uniform spacing between the dilution apertures 62 and 64 in the two rows of dilution apertures 58 and 60 respectively.
Each triangular cross-sectional shaped dilution aperture 62 in the first row of dilution apertures 58 is positioned circumferentially between two adjacent triangular cross-sectional shaped dilution apertures 64 in the second row of dilution apertures 60 and thus each triangular cross-sectional shaped dilution aperture 64 in the second row of dilution apertures 60 is positioned circumferentially between two adjacent triangular cross-sectional shaped dilution apertures 62 in the first row of dilution apertures 58.
Thus, it can be seen that the sides 64D of the triangular cross-sectional dilution apertures 64 of the second row of dilution apertures 60 are arranged in a first plane A perpendicular to the axis X of the gas turbine engine 10, the corners 62A of the triangular cross-sectional dilution apertures 62 of the first row of dilution apertures 58 are arranged in a second plane B perpendicular to the axis X of the gas turbine engine 10, the corners 64A of the triangular cross-sectional dilution apertures 64 of the second row of dilution apertures 60 are arranged in a third plane C perpendicular to the axis X of the gas turbine engine 10 and the sides 62D of the triangular cross-sectional dilution apertures 62 of the first row of dilution apertures 58 are arranged in a fourth plane D perpendicular to the axis X of the gas turbine engine 10. The first plane A is axially upstream of the second plane B, the second plane is axially upstream of the third plane C and the third plane C is axially upstream of the fourth plane D. Similarly the radially outer annular wall structure 42 has at least two rows of dilution apertures 58' and 60' and the two rows of dilution apertures 58' and 60' are spaced apart axially along the radially outer annular wall 42. The row of dilution apertures 60' is axially upstream of the row of dilution apertures 58'. The rows of dilution apertures 58' and 60' extend through the third annular wall 50 and the fourth annular wall 52.
Each row of dilution apertures 58' and 60' comprises a plurality of circumferentially spaced dilution apertures 62' and 64' respectively and each dilution aperture 62' and 64' has a substantially triangular cross-sectional shape. The dilution apertures 62' and 64' in the adjacent rows of dilution apertures 58' and 60' respectively are staggered circumferentially. The rows of dilution apertures 58' and 60' in the radially outer annular wall structure 42 are arranged in a similar manner to the rows of dilution apertures 58 and 60 in the radially inner annular wall structure 40.
Figure 4 shows an alternative arrangement of the two rows of dilution apertures 58A and 60A. In this arrangement the corner 62A of each triangular cross-sectional shaped dilution aperture 62 in one of the adjacent rows of dilution apertures 58A is arranged axially in the same plane as the sides 64D of the triangular cross-sectional shaped dilution apertures 64 in the other of the adjacent rows of triangular shaped dilution apertures 60A. The corner 64A of each triangular cross-sectional shaped dilution aperture 64 in the other of the adjacent rows of dilution apertures 60A is arranged axially in the same plane as the sides 62D of the triangular cross-sectional shaped dilution apertures 62 in the one of the adjacent rows of triangular shaped dilution apertures 58A. The triangular cross-sectional shaped dilution apertures 62 and 64 are equilateral triangles, but the triangular cross-sectional shaped dilution apertures may be right angle triangles, isosceles triangles or scalene triangles.
Each triangular cross-sectional shaped dilution aperture 62 in the first row of dilution apertures 58A is positioned circumferentially between two adjacent triangular cross-sectional shaped dilution apertures 64 in the second row of dilution apertures 60A and thus each triangular cross-sectional shaped dilution aperture 64 in the second row of dilution apertures 60A is positioned circumferentially between two adjacent triangular cross-sectional shaped dilution apertures 62 in the first row of dilution apertures 58A.
Thus, it can be seen that the sides 64D of the triangular cross-sectional dilution apertures 64 of the second row of dilution apertures 60A are arranged in a first plane E perpendicular to the axis X of the gas turbine engine 10, the corners 62A of the triangular cross-sectional dilution apertures 62 of the first row of dilution apertures 58A are arranged in the first plane F perpendicular to the axis X of the gas turbine engine 10, the corners 64A of the triangular cross-sectional dilution apertures 64 of the second row of dilution apertures 60A are arranged in a second plane F perpendicular to the axis X of the gas turbine engine 10, the sides 62D of the triangular cross-sectional dilution apertures 62 of the first row of dilution apertures 58A are arranged in the second plane F perpendicular to the axis X of the gas turbine engine 10 and the first plane A is axially upstream of the second plane B. Figure 5 shows an alternative arrangement of the two rows of dilution apertures 58B and 60B. This arrangement is similar to the arrangement in figure 4 but the triangular cross-sectional shaped dilution apertures 162 and 164 are keyhole shaped. It may be possible to provide key hole shaped dilution apertures 162 and 164 in place of the triangular cross-sectional shaped dilution apertures in figure 3.
Figure 6 shows an alternative arrangement of the two rows of dilution apertures 58C and 600. This arrangement is similar to the arrangement in figure 3 but the triangular cross-sectional shaped dilution apertures 262 and 264 are right angle triangles. It may be possible to provide right angle triangle dilution apertures 262 and 264 in place of the triangular cross-sectional shaped dilution apertures in figure 4.
In all of the figures the minimum distance d between the triangular cross-sectional shaped dilution apertures in the adjacent rows of dilution apertures are the same.
Although the present invention has been described with reference to an annular combustion chamber having a radially inner annular wall and a radially outer annular wall, it is equally applicable to a tubular combustion chamber having a single annular wall. Although the present invention has been described with reference to a wall of the combustion chamber having two rows of dilution apertures it may be applicable to a combustion chamber having three, four or more rows of dilution apertures.
Although the present invention has been described with reference to a combustion chamber with the, or each, wall comprises an inner wall and an outer wall it is equally applicable to a combustion chamber in which the, or each, wall comprises a single wall and the single wall may be a solid wall with Z type cooling rings or a laminated wall for example lamilloy (RTM) or filmply.
Although the present invention has been described with reference to a gas turbine engine combustion chamber it may be applicable to other combustion chambers.
The advantage of the present invention is that the axial distance taken up by the array, two rows, of dilution apertures in each wall of the combustion chamber is reduced compared to the use of two rows of circular cross-sectional dilution apertures because more efficient use is made of the space. This is despite the minimum distance between the dilution apertures being the same. Calculations indicate that 20% more mass flow of dilution air may flow through a 30% shorter axial distance in the array of dilution apertures of the present invention compared to the use of two rows of circular cross-sectional dilution apertures. Another advantage of the present invention is that there will be better quenching of the rich burn combustion process in the combustion chamber and therefore there will be a reduction in nitrous oxide emissions due to the more efficient use of space.
Although the present invention has been described with reference to triangular cross-sectional shape dilution apertures, it may be possible to use rhombus, or diamond, cross-sectional shape dilution apertures or pentagonal cross-sectional shape dilution apertures.
Although the present invention has been described with reference to two rows of dilution apertures it may be possible to use three rows of dilution apertures, however the use of two rows is preferred because the apertures have greater dimensions and have better penetration into the combustion chamber and produce better mixing with the combustion gases in the combustion chamber.
Claims (18)
- CLAIMS1. A combustion chamber comprising at least one annular wall, the at least one annular wall having at least two rows of dilution apertures, each row of dilution apertures comprising a plurality of circumferentially spaced dilution apertures, each dilution aperture having a substantially polygonal cross-sectional shape, the dilution apertures in adjacent rows of dilution apertures being staggered circumferentially, and a corner of each polygonal cross-sectional shaped dilution aperture in one of the adjacent rows of dilution apertures being axially upstream of a corner of each polygonal cross-sectional shaped dilution aperture in the other of the adjacent rows of dilution apertures.
- 2. A combustion chamber as claimed in claim 1 wherein each dilution aperture having a substantially triangular cross-sectional shape, the dilution apertures in adjacent rows of dilution apertures being staggered circumferentially, and a corner of each triangular cross-sectional shaped dilution aperture in one of the adjacent rows of dilution apertures being axially upstream of a corner of each triangular cross-sectional shaped dilution aperture in the other of the adjacent rows of dilution apertures.
- 3. A combustion chamber as claimed in claim 2 wherein one of the sides of each triangular cross-sectional shaped dilution aperture in one of the adjacent rows of dilution apertures extends circumferential ly.
- 4. A combustion chamber as claimed in claim 2 or claim 3 wherein one of the sides of each triangular cross-sectional shaped dilution aperture in the other of the adjacent rows of dilution apertures extends circumferentially.
- 5. A combustion chamber as claimed in claim 2, claim 3 or claim 4 wherein the triangular cross-sectional shaped dilution apertures in the adjacent rows of dilution apertures have identical shapes.
- 6. A combustion chamber as claimed in claim 2, claim 3, claim 4 or claim S wherein the triangular cross-sectional shaped dilution apertures in the adjacent rows of dilution apertures have identical cross-sectional areas.
- 7. A combustion chamber as claimed in any of claims 2 to 6 wherein the triangular cross-sectional shaped dilution apertures are right angle triangles, equilateral triangles, isosceles triangles or scalene triangles.
- 8. A combustion chamber as claimed in any of claims 2 to 7 wherein the triangular cross-sectional shaped dilution apertures have rounded corners.
- 9. A combustion chamber as claimed in claims 2 to 6 wherein the triangular cross-sectional shaped dilution apertures are keyhole shaped.
- 10. A combustion chamber as claimed in any of claims 2 to 9 wherein the corner of each triangular cross-sectional shaped dilution aperture in one of the adjacent rows of dilution apertures is arranged axially in the same plane as the sides of the triangular cross-sectional shaped dilution apertures in the other of the adjacent rows of triangular shaped dilution apertures.
- 11. A combustion chamber as claimed in claim 10 wherein the corner of each triangular cross-sectional shaped dilution aperture in the other of the adjacent rows of dilution apertures is arranged axially in the same plane as the sides of the triangular cross-sectional shaped dilution apertures in the one of the adjacent rows of triangular shaped dilution apertures.
- 12. A combustion chamber as claimed in any of claims 2 to 11 wherein the base of each triangular cross-sectional shaped dilution aperture in the adjacent rows of triangular cross-sectional shaped dilution apertures extends circumferentially and each triangular cross-sectional shaped dilution aperture in one of the rows of triangular cross-sectional shaped dilution apertures is positioned circumferentially between two adjacent triangular cross-sectional shaped dilution apertures in the other row of triangular cross-sectional shaped dilution apertures.
- 13. A combustion chamber as claimed in any of claims 2 to 12 wherein each side of each triangular cross-sectional shaped dilution aperture in one of the rows of triangular cross-sectional shaped dilution apertures is parallel with one of the sides of one of the two adjacent triangular cross-sectional shaped dilution apertures in the adjacent row of triangular cross-sectional shaped dilution apertures.
- 14. A combustion chamber as claimed in any of claims 1 to 13 wherein the combustion chamber has a radially inner annular wall and a radially outer annular wall.
- 15. A combustion chamber as claimed in claim 14 wherein the radially inner annular wall andlor the radially outer annular wall has at least two rows of dilution apertures.
- 16. A combustion chamber as claimed in any of claims 1 to 15 wherein the combustion chamber is a gas turbine engine combustion chamber.
- 17. A combustion chamber as claimed in claim 16 wherein the combustion chamber is a tubular combustion chamber or an annular combustion chamber.
- 18. A combustion chamber substantially as hereinbefore described with reference to and as shown in any of figures 2 to 6 of the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB201306124A GB2512642A (en) | 2013-04-05 | 2013-04-05 | A combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB201306124A GB2512642A (en) | 2013-04-05 | 2013-04-05 | A combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB201306124D0 GB201306124D0 (en) | 2013-05-22 |
| GB2512642A true GB2512642A (en) | 2014-10-08 |
Family
ID=48483352
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB201306124A Withdrawn GB2512642A (en) | 2013-04-05 | 2013-04-05 | A combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2512642A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11686473B2 (en) | 2021-11-11 | 2023-06-27 | General Electric Company | Combustion liner |
| US11754284B2 (en) | 2021-11-11 | 2023-09-12 | General Electric Company | Combustion liner |
| US11788726B2 (en) | 2021-12-06 | 2023-10-17 | General Electric Company | Varying dilution hole design for combustor liners |
| US11808454B2 (en) | 2021-11-11 | 2023-11-07 | General Electric Company | Combustion liner |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070044474A1 (en) * | 2005-08-31 | 2007-03-01 | Snecma | Combustion chamber for a turbomachine |
-
2013
- 2013-04-05 GB GB201306124A patent/GB2512642A/en not_active Withdrawn
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070044474A1 (en) * | 2005-08-31 | 2007-03-01 | Snecma | Combustion chamber for a turbomachine |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11686473B2 (en) | 2021-11-11 | 2023-06-27 | General Electric Company | Combustion liner |
| US11754284B2 (en) | 2021-11-11 | 2023-09-12 | General Electric Company | Combustion liner |
| US11808454B2 (en) | 2021-11-11 | 2023-11-07 | General Electric Company | Combustion liner |
| US11788726B2 (en) | 2021-12-06 | 2023-10-17 | General Electric Company | Varying dilution hole design for combustor liners |
Also Published As
| Publication number | Publication date |
|---|---|
| GB201306124D0 (en) | 2013-05-22 |
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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) |