US5966937A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Radial inlet swirler with twisted vanes for fuel injector
Assignee: RTX Corp
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Filing: 1997-10-09
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Granted: 1999-10-19
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Expires: 2017-10-09
Abstract
Abstract The fuel injector for a combustor of a gas turbine engine of the high shear design type is configured to include two swirlers with passages where the vanes in the inner swirler of the inner swirler in the passage which is closest to the centerline of the fuel nozzle includes a judiciously located twist and together with the proper flow ratio between the two swirl passages and the proper swirl angle of the flow stream in each of the passages provide an enhanced fuel injector with improved lean blowout and high altitude relight characteristics while assuring a stable recirculation region in the combustion zone.
Inventors
- 👤 Charles B. Graves
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 14:29
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/10; F23R3/12; F23R3/14; F23C; F23C7/00; F23C7/002; F23C7/004; F23D; F23D2900/00; F23D2900/11101
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
179 words
A high shear designed fuel injector for a combustor of a gas turbine engine comprising a fuel nozzle supported at an inlet of said combustor, a first radial inlet swirler mounted on said fuel nozzle and including a first passage for flowing air into the combustor and being coaxially disposed relative to said fuel nozzle, a second radial inlet swirler mounted adjacent to said first radial swirler and including a second passage for flowing additional air into the combustor and being concentrically disposed relative to said first passage, said first radial inlet swirler having circumferentially disposed vanes, said vanes having a top section and a base section each having a swirl angle, the base section being attached to a radially extending wall of said first or second passage, said vanes being configured with a twist, said twist being about a central axis extending from and changing the swirl angle from the top section to the base section to offset the swirl to a higher level that the swirl would be without twisting the vanes to produce a Rankine vortex.
Claim 2
Dependent Claim
179 words
A high shear designed fuel injector for a combustor of a gas turbine engine comprising a fuel nozzle supported at an inlet of said combustor, a first radial inlet swirler mounted on said fuel nozzle and including a first passage for flowing air into the combustor and being coaxially disposed relative to said fuel nozzle, a second radial inlet swirler mounted adjacent to said first radial swirler and including a second passage for flowing additional air into the combustor and being concentrically disposed relative to said first passage, said first radial inlet swirler having circumferentially disposed vanes, said vanes having a top section and a base section each having a swirl angle, the base section being attached to a radially extending wall of said first or second passage, said vanes being configured with a twist, said twist being about a central axis extending from and changing the swirl angle from the top section to the base section to offset the swirl to a higher level that the swirl would be without twisting the vanes to produce a Rankine vortex.
Claim 3
Dependent Claim
24 words
A high shear designed fuel injector as claimed in claim 1 wherein said second swirler includes circumferentially spaced vanes that have no twist configuration.
Claim 4
Dependent Claim
29 words
A high shear designed fuel injector as claimed in claim 2 wherein a majority of the air in the first passage and second passage is in the first passage.
Claim 5
Dependent Claim
37 words
A high shear designed fuel injector as claimed in claim 3 wherein the amount of air in the first passage is substantially equal to 70%-92% of the total air flow in the first passage and second passage.
Claim 6
Dependent Claim
31 words
A high shear designed fuel injector as claimed in claim 4 wherein a bulk swirl angle of air at a discharge of said second passage is substantially equal to between 70°-75°.
Claim 7
Dependent Claim
44 words
A high shear designed fuel injector as claimed in claim 5 where a swirl angle of the air at a discharge of said first passage in a free vortex region is progressively larger from a center of the fuel injector to a prefilmer wall.
Claim 8
Dependent Claim
59 words
A high shear designed fuel injector as claimed in claim 6 wherein the swirl angle of the air closest to said center at the discharge end of said first passage is substantially equal to 90° and the swirl angle of the air closest to the prefilmer wall at the discharge of said first passage is substantially equal to 25°.
Claim 9
Dependent Claim
35 words
A high shear designed fuel injector as claimed in claim 1 wherein the base of the vane angle is substantially equal to 16° and the twist has an angular spread of 8° above said base.
Claim 10
Dependent Claim
23 words
A high shear designed fuel injector as claimed in claim 1 wherein the spread from top to bottom is substantially equal to 50%.
Claim 11
Dependent Claim
150 words
A high shear designed fuel injector for a combustor of a gas turbine engine comprising a fuel nozzle mounted in a front end of said combustor, a first radial inlet swirler including a first passage for flowing air into the combustor and being coaxially disposed relative to said fuel nozzle and supported thereto, a second radial inlet swirler including a second passage for flowing additional air into the combustor and being concentrically disposed relative to said first passage and being mounted thereto, said first swirler having circumferentially disposed vanes having a top section and a base attached to a radially extending wall of said first or second passage, said vanes being configured with a twist extending from the top section to said base, the base having a vane angle substantially equal to 16° and the twist having an angular spread of 8° above said base for producing a Rankine vortex.
Claim 12
Dependent Claim
150 words
A high shear designed fuel injector for a combustor of a gas turbine engine comprising a fuel nozzle mounted in a front end of said combustor, a first radial inlet swirler including a first passage for flowing air into the combustor and being coaxially disposed relative to said fuel nozzle and supported thereto, a second radial inlet swirler including a second passage for flowing additional air into the combustor and being concentrically disposed relative to said first passage and being mounted thereto, said first swirler having circumferentially disposed vanes having a top section and a base attached to a radially extending wall of said first or second passage, said vanes being configured with a twist extending from the top section to said base, the base having a vane angle substantially equal to 16° and the twist having an angular spread of 8° above said base for producing a Rankine vortex.
Claim 13
Dependent Claim
37 words
A high shear designed fuel injector as claimed in claim 10 wherein the amount of air in the first passage is substantially equal to 70%-92% of the total air flow in the first passage and second passage.
Claim 14
Dependent Claim
31 words
A high shear designed fuel injector as claimed in claim 11 wherein a bulk swirl angle of air at a discharge of said second passage is substantially equal to between 70°-75°.
Claim 15
Dependent Claim
44 words
A high shear designed fuel injector as claimed in claim 12 where a swirl angle of the air at a discharge of said first passage in a free vortex region is progressively larger from a center of the fuel injector to a prefilmer wall.
Claim 16
Dependent Claim
59 words
A high shear designed fuel injector as claimed in claim 13 wherein the swirl angle of the air closest to said center at the discharge end of said first passage is substantially equal to 90° and the swirl angle of the air closest to the prefilmer wall at the discharge of said first passage is substantially equal to 25°.
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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) | 2002-10-18 | 2003-04-19 | 2003-10-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2006-10-18 | 2007-04-19 | 2007-10-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2010-10-18 | 2011-04-19 | 2011-10-19 | $7700.00 | Window Closed / Lapsed |