US5331814A
Expired / Lapsed
US
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Gas turbine combustion chamber with multiple fuel injector arrays
Assignee: Safran Aircraft Engines SAS
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Filing: 1993-07-16
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Granted: 1994-07-26
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Expires: 2013-07-16
Abstract
Abstract A gas turbine engine combustion chamber is disclosed having multiple sets of fuel injectors. A set of first fuel injectors are arranged in two radially inner and outer generally circular first arrays such that the fuel injectors of one array are located circumferentially between the fuel injectors of the other array. The combustion chamber also includes a set of second fuel injectors which are also arranged in two generally circular, radially inner and outer arrays such that, in each array, the second fuel injectors are located circumferentially between the first fuel injectors. In a circumferential direction, the positions of the first and second fuel injectors vary between the radially outward array and the radially inward array. One set of fuel injectors may operate under idle and low power operating conditions, while the other set of fuel injectors inject fuel into the combustion chamber during full power take off or cruise operations. Since the radial positions of adjacent fuel injectors in each set vary in a radial direction around the circumference of the combustion chamber, the radial temperature variations are eliminated.
Inventors
- 👤 Denis J. M. Sandelis
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 19:16
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/34
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
263 words
A combustion chamber for a gas turbine engine, the combustion chamber having a generally annular configuration about a central axis and having an outlet and being defined by inner and outer axial walls and an upstream end wall extending between the inner and outer walls, comprising: a) a plurality of first fuel injectors to inject first sprays of fuel directly into the combustion chamber during a first operational mode of a gas turbine engine, the plurality of first fuel injectors arranged in inner and outer first fuel injector arrays about the central axis, the first fuel injectors of each array being circumferentially spaced apart and located such that the first fuel injectors of one first fuel injector array are disposed circumferentially between first fuel injectors of the other first fuel injector array; b) a plurality of second fuel injectors to inject second sprays of fuel into the combustion chamber during a second operational mode of the gas turbine engine, the plurality of second fuel injectors arranged in inner and outer second fuel injector arrays about the central axis, the second fuel injector of each array being circumferentially spaced apart and located such that the second fuel injectors of one second fuel injector array are disposed circumferentially between second fuel injectors of the other second fuel injector array and c) first wall means extending axially into the combustion Chamber from the upstream end wall and having side edges attached to one of the inner and outer walls so as to define a plurality of chambers into which only the second fuel injectors inject fuel.
Claim 2
Dependent Claim
263 words
A combustion chamber for a gas turbine engine, the combustion chamber having a generally annular configuration about a central axis and having an outlet and being defined by inner and outer axial walls and an upstream end wall extending between the inner and outer walls, comprising: a) a plurality of first fuel injectors to inject first sprays of fuel directly into the combustion chamber during a first operational mode of a gas turbine engine, the plurality of first fuel injectors arranged in inner and outer first fuel injector arrays about the central axis, the first fuel injectors of each array being circumferentially spaced apart and located such that the first fuel injectors of one first fuel injector array are disposed circumferentially between first fuel injectors of the other first fuel injector array; b) a plurality of second fuel injectors to inject second sprays of fuel into the combustion chamber during a second operational mode of the gas turbine engine, the plurality of second fuel injectors arranged in inner and outer second fuel injector arrays about the central axis, the second fuel injector of each array being circumferentially spaced apart and located such that the second fuel injectors of one second fuel injector array are disposed circumferentially between second fuel injectors of the other second fuel injector array and c) first wall means extending axially into the combustion Chamber from the upstream end wall and having side edges attached to one of the inner and outer walls so as to define a plurality of chambers into which only the second fuel injectors inject fuel.
Claim 3
Dependent Claim
27 words
The combustion chamber of claim 1 wherein the inner first and second fuel injector arrays extend generally circularly about the central axis and have substantially equal radii.
Claim 4
Dependent Claim
27 words
The combustion chamber of claim 2 wherein the outer first and second fuel injector arrays extend generally circularly about the central axis and have substantially equal radii.
Claim 5
Dependent Claim
39 words
The combustion chamber of claim 3 wherein the arrays of first and second fuel injectors are oriented such that a first fuel injector and a second fuel injector are located on a line extending radially from the central axis.
Claim 6
Dependent Claim
36 words
The combustion chamber of claim 1 having an axial length L between the upstream end wall and the outlet, wherein the axial length Lw of the first wall means is between 0.15 L and 0.30 L.
Claim 7
Dependent Claim
27 words
The combustion chamber of claim 1 having an axial gas flow direction wherein the the first wall means extends substantially parallel to the axial gas flow direction.
Claim 8
Dependent Claim
38 words
The combustion chamber of claim 1 further comprising second wall means extending into the combustion chamber from the upstream wall spaced from and extending substantially parallel to the first wall means so as to define a space therebetween.
Claim 9
Dependent Claim
32 words
The combustion chamber of claim 7 further comprising swirl means operatively associated with each fuel injector so as impart a circular swirling movement to the fuel sprays emanating from each fuel injector.
Claim 10
Dependent Claim
82 words
The combustion chamber of claim 8 wherein the space between the first and second wall means communicates with an oxidizer supply and further comprising a plurality of first holes defined by the first wall mans so as to allow communication from the space between the first and second walls into the combustion chamber, the plurality of first holes oriented such that flow into the combustion chamber is in the same direction as the swirling fuel spray emanating from an adjacent fuel injector.
Claim 11
Dependent Claim
71 words
The combustion chamber of claim 9 further comprising a plurality of second holes defined by the second wall means so as to allow oxidizer communication from the space between the first and second wall means into the chamber defined by the first wall means, the plurality of second holes oriented such that flow into the chamber is generally in the same direction as the swirling fuel sprays located in the chamber.
Claim 12
Dependent Claim
28 words
The combustion chamber of claim 7 wherein the first wall means extends radially into the combustion chamber to substantially midway between the inner and outer fuel injector arrays.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1997-07-25 | 1998-01-24 | 1998-07-26 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-07-25 | 2002-01-24 | 2002-07-26 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-07-25 | 2006-01-24 | 2006-07-26 | $7700.00 | Window Closed / Lapsed |