US4720971A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method for distributing augmentor fuel
Assignee: RTX Corp
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Filing: 1986-08-29
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Granted: 1988-01-26
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Expires: 2006-08-29
Abstract
Abstract A method for distributing a flow of fuel over the gas flow area of a gas turbine engine includes the steps of dividing the gas flow area into a plurality of sector shaped sub-areas (48), (50), (52), (54) disposed within a surrounding, annular sub-area (46) which is in turn disposed adjacent the augmentor wall (12). During operation, the method according to the present invention distributes the fuel over one or more of the sub-areas (46-54) in response to the current rate of fuel flow. At the lowest and intermediate fuel flow rates, fuel is distributed only over one or more of the sector shaped sub-areas (48-54). Only at the very highest rates of augmentor fuel flow is fuel distributed finally in the outer annular sub-area (46).
Inventors
- 👤 Thomas L. DuBell
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 03:02
CPC Classifications
F; F02; F02K; F02K3/00; F02K3/08; F02K3/10; F02C; F02C3/00; F02C3/14
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
191 words
A method for distributing a flow of fuel over a circular flow area in a gas turbine engine augmentor, the flow of fuel having a current flow rate variable over a range of flow rates, comprising the steps of: dividing the augmentor flow area into a plurality of sub-areas, one sub-area being annular in shape and disposed adjacent the augmentor interior surface, and the other sub-areas being sectors of the circular area remaining within the one annular sub-area; dividing the range of flow rates into a series of sub-ranges, the series comprising a pilot sub-range including the initial and lowest augmentor fuel flow rates, a full thrust sub-range including the highest and maximum augmentor fuel flow rates, and one or more intermediate sub-ranges including all augmentor fuel flow rates between the pilot and full thrust sub-ranges; allocating one or more sub-areas to each fuel flow rate sub-range, the sector sub-areas being sub-ranges, and the annular sub-area being allocated to only the full thrust sub-range; and distributing the flow of fuel to those sub-areas allocated to sub-ranges corresponding to fuel flow rates up to and including the current rate of fuel flow.
Claim 2
Independent Claim
191 words
A method for distributing a flow of fuel over a circular flow area in a gas turbine engine augmentor, the flow of fuel having a current flow rate variable over a range of flow rates, comprising the steps of: dividing the augmentor flow area into a plurality of sub-areas, one sub-area being annular in shape and disposed adjacent the augmentor interior surface, and the other sub-areas being sectors of the circular area remaining within the one annular sub-area; dividing the range of flow rates into a series of sub-ranges, the series comprising a pilot sub-range including the initial and lowest augmentor fuel flow rates, a full thrust sub-range including the highest and maximum augmentor fuel flow rates, and one or more intermediate sub-ranges including all augmentor fuel flow rates between the pilot and full thrust sub-ranges; allocating one or more sub-areas to each fuel flow rate sub-range, the sector sub-areas being sub-ranges, and the annular sub-area being allocated to only the full thrust sub-range; and distributing the flow of fuel to those sub-areas allocated to sub-ranges corresponding to fuel flow rates up to and including the current rate of fuel flow.
Claim 3
Dependent Claim
55 words
The method as recited in claim 1, wherein the step of dividing the range of fuel flow rates into a series of sub-ranges includes the step of: sizing each successive flow rate sub-range in the series responsive to the next lower sub-range for avoiding an over pressure in the augmentor upon transition between adjacent sub-ranges.
Claim 4
Dependent Claim
97 words
The method as recited in claim 1, wherein the step of allocating one or more augmentor flow sub-areas to each of the fuel flow rate sub-ranges includes the step of: allocating a first sector sub-area to the pilot sub-range; allocating second and third sector sub-areas to a first intermediate sub-range adjacent the pilot sub-range, the second and third sub-areas each disposed circumferentially opposite the first sub-area and adjacent thereto; and allocating a fourth sector sub-area to a second intermediate sub-range superadjacent the first intermediate sub-range, the fourth sub-area being circumferentially adjacent to at least the second sub-area.
Claim 5
Dependent Claim
33 words
The method as recited in claim 1, further comprising the step of: providing a means for igniting the distributed fuel only in a first sub-area allocated to the pilot fuel flow rate sub-range.
Claim 6
Dependent Claim
63 words
The method as recited in claim 1, wherein the step of allocating one or more augmentor flow sub-areas to each fuel flow rate sub-range further includes the step of: allocating to successively higher flow rate sub-ranges only those sub-areas adjacent to sub-areas allocated to lower fuel flow rate sub-ranges, whereby the flow of fuel is always distributed over a group of continguous sub-areas.
Claim 7
Independent Claim
95 words
A method for the staged distribution of fuel over the gas flow area of a gas turbine engine augmentor, comprising the steps of distributing the fuel over one or more sector shaped sub-areas disposed within an annular sub-area disposed adjacent the interior surface of the augmentor; determining the number of fueled sector shaped sub-areas responsive to the current rate of augmentor fuel flow for achieving a local fuel-air ratio in each fueled sub-area corresponding to a stable combustion reaction downstream thereof; and finally distributing fuel over the outer annular sub-area for achieving maximum augmentor performance.
Claim 8
Independent Claim
95 words
A method for the staged distribution of fuel over the gas flow area of a gas turbine engine augmentor, comprising the steps of distributing the fuel over one or more sector shaped sub-areas disposed within an annular sub-area disposed adjacent the interior surface of the augmentor; determining the number of fueled sector shaped sub-areas responsive to the current rate of augmentor fuel flow for achieving a local fuel-air ratio in each fueled sub-area corresponding to a stable combustion reaction downstream thereof; and finally distributing fuel over the outer annular sub-area for achieving maximum augmentor performance.
Claim 9
Dependent Claim
33 words
The method as recited in claim 6, further comprising the step of: distributing the fuel over only adjacent sub-areas in response to increasing fuel flow, the fueled sub-areas always forming a contiguous grouping.
References Cited (Backward Citations)
US2984970A
Cited
US2887845A
Cited
US3719042A
Cited
US3698186A
Cited
US4315401A
Cited
US4423595A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1991-01-25 | 1991-07-27 | 1992-01-26 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1995-01-25 | 1995-07-27 | 1996-01-26 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1999-01-25 | 1999-07-27 | 2000-01-26 | $7700.00 | Window Closed / Lapsed |