Patent US4045957A successfully refreshed from Google Patents.
US4045957A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Combined guide vane and mixer for a gas turbine engine
Assignee: RTX Corp
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Filing: 1976-02-20
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Granted: 1977-09-06
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Expires: 1996-02-20
Abstract
Abstract The multi-lobed mixer downstream of the turbine of a gas turbine engine is constructed to include the exit guide vanes for the turbine carried on the inner diameter of the mixer so as to prevent diffusing with a consequential reduction of pressure losses and engine weight.
Inventors
- 👤 Vincent J. DiSabato
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 08:12
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/38; F02K1/386; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
128 words
A mixer for a fan jet engine power plant located downstream of the turbine for mixing the flow from the turbine and the fan, comprising a sinuous circumferentially shaped body having inner and outer lobes, the inner lobes being closer to the axis of the engine and having a bottom wall, the improvement comprising flow guide means having an upstream portion aligned with the direction of approaching flow and, a downstream portion to circumferentially turn the flow, the flow guide means disposed adjacent the bottom wall extending within the body of the mixer to turn the flow exhausting from said turbine in a predominantly circumferential direction whereby the turning of the turbine exhaust is accomplished within the mixer prior to being mixed with the fan discharge air flow.
Claim 2
Dependent Claim
128 words
A mixer for a fan jet engine power plant located downstream of the turbine for mixing the flow from the turbine and the fan, comprising a sinuous circumferentially shaped body having inner and outer lobes, the inner lobes being closer to the axis of the engine and having a bottom wall, the improvement comprising flow guide means having an upstream portion aligned with the direction of approaching flow and, a downstream portion to circumferentially turn the flow, the flow guide means disposed adjacent the bottom wall extending within the body of the mixer to turn the flow exhausting from said turbine in a predominantly circumferential direction whereby the turning of the turbine exhaust is accomplished within the mixer prior to being mixed with the fan discharge air flow.
Claim 3
Dependent Claim
33 words
A mixer as claimed in claim 1 including a plug having an axisymmetrical shape including a wider diameter portion intermediate its ends, and circumferentially bearing against a circumferential portion of said inner lobes.
Claim 4
Dependent Claim
18 words
A mixer as claimed in claim 1 in which said guide means are a plurality of guide vanes.
Claim 5
Dependent Claim
22 words
A mixer as claimed in claim 3 in which said guide vanes are integral with the bottom wall of said inner lobes.
Claim 6
Dependent Claim
183 words
A mixer for a fan jet engine power plant located downstream of the turbine for mixing the flow from the turbine and the fan comprising a circular hollow body portion and a sinuous circumferentially shaped body portion extending axially therefrom, said sinuous shaped body portion defining inner and outer lobes, the inner lobes being closer to the axis of the engine and having a bottom wall, the improvement comprising a plug-like element extending through said mixer having a larger diameter portion bearing against the inner lobes through a transverse plane and a smaller diameter portion defining an annular space adjacent the circular portion, guide-like member disposed adjacent the bottom wall extending within the body of the mixer and having a leading edge extending into the hollow portion of said circular body portion aligned with the direction of approaching flow, and a trailing edge portion to circumferentially turn the flow, whereby the turning of the turbine exhaust in a predominantly circumferential direction is accomplished within the mixer prior to being mixed with the fan discharge air flow at the exhaust end of said mixer.
Claim 7
Dependent Claim
183 words
A mixer for a fan jet engine power plant located downstream of the turbine for mixing the flow from the turbine and the fan comprising a circular hollow body portion and a sinuous circumferentially shaped body portion extending axially therefrom, said sinuous shaped body portion defining inner and outer lobes, the inner lobes being closer to the axis of the engine and having a bottom wall, the improvement comprising a plug-like element extending through said mixer having a larger diameter portion bearing against the inner lobes through a transverse plane and a smaller diameter portion defining an annular space adjacent the circular portion, guide-like member disposed adjacent the bottom wall extending within the body of the mixer and having a leading edge extending into the hollow portion of said circular body portion aligned with the direction of approaching flow, and a trailing edge portion to circumferentially turn the flow, whereby the turning of the turbine exhaust in a predominantly circumferential direction is accomplished within the mixer prior to being mixed with the fan discharge air flow at the exhaust end of said mixer.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-09-05 | 1981-03-07 | 1981-09-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-09-05 | 1985-03-07 | 1985-09-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-09-05 | 1989-03-07 | 1989-09-06 | $7700.00 | Window Closed / Lapsed |