US4128995A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method and apparatus for stabilizing an augmenter system
Assignee: General Electric Co
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Filing: 1976-10-18
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Granted: 1978-12-12
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Expires: 1996-10-18
Abstract
Abstract A turbine is stabilized in high speed, high altitude flight conditions by reducing the maximum augmenter fuel/air ratio in response to certain pressure and temperature conditions. Temperatures and pressures indicative of those at the combustor are sensed and the augmenter fuel schedule is accordingly modified to a level which provides reduced fuel/air ratios and stable burning conditions.
Inventors
- 👤 Peter D. Toot
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 23:14
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/46; F02K1/48
Claims Analysis
Total Claims: 26
Claim 1
Independent Claim
111 words
In a jet engine combustion apparatus, an improved fuel control system of the type for scheduling the fuel/air ratio to the combustion apparatus in response to predetermined engine operating parameters, wherein the improvement comprises: a. means for sensing pressures indicative of the air pressure in said combustor; b. means for sensing temperatures representative of the air temperature in said combustor; c. means for generating in terms of one of the engine operating parameters a schedule indicative of the combustor rich stability limit; and d. means for maintaining operation of the engine within the rich stability limit by modifying the fuel/air ratio schedule in response to both said sensed pressures and temperatures.
Claim 2
Dependent Claim
111 words
In a jet engine combustion apparatus, an improved fuel control system of the type for scheduling the fuel/air ratio to the combustion apparatus in response to predetermined engine operating parameters, wherein the improvement comprises: a. means for sensing pressures indicative of the air pressure in said combustor; b. means for sensing temperatures representative of the air temperature in said combustor; c. means for generating in terms of one of the engine operating parameters a schedule indicative of the combustor rich stability limit; and d. means for maintaining operation of the engine within the rich stability limit by modifying the fuel/air ratio schedule in response to both said sensed pressures and temperatures.
Claim 3
Dependent Claim
32 words
An improved fuel control system as set forth in claim 1 wherein the jet engine includes a compressor and said pressure sensing means is located at the discharge end of the compressor.
Claim 4
Dependent Claim
29 words
An improved fuel control system as set forth in claim 1 wherein the jet engine includes a compressor and said temperature sensing means is located forward of the compressor.
Claim 5
Dependent Claim
31 words
An improved fuel control system as set forth in claim 3 and including a jet engine inlet, wherein said temperature sensing means is located in the inlet to the jet engine.
Claim 6
Dependent Claim
18 words
An improved fuel control system as set forth in claim 1 wherein said combustion apparatus comprises an afterburner.
Claim 7
Dependent Claim
29 words
An improved fuel control system as set forth in claim 1 wherein said modifying means includes means for generating a pressure schedule in response to said temperature sensing means.
Claim 8
Dependent Claim
25 words
An improved fuel control system as set forth in claim 6 and including comparator means for comparing said generated pressure schedule with said sensed pressures.
Claim 9
Independent Claim
90 words
A method of stabilizing a fuel control system of the type which schedules the fuel/air ratio to a combustion apparatus in response to certain engine operating parameters, comprising the steps of: a. sensing pressures representative of the air pressure in the combustor; b. sensing temperatures representative of the air temperatures in said combustor; c. generating a schedule indicative of the combustor rich stability limit; and d. maintaining operation of the engine within the rich stability limit by modifying the fuel/air ratio in response to both said sensed pressures and temperatures.
Claim 10
Independent Claim
90 words
A method of stabilizing a fuel control system of the type which schedules the fuel/air ratio to a combustion apparatus in response to certain engine operating parameters, comprising the steps of: a. sensing pressures representative of the air pressure in the combustor; b. sensing temperatures representative of the air temperatures in said combustor; c. generating a schedule indicative of the combustor rich stability limit; and d. maintaining operation of the engine within the rich stability limit by modifying the fuel/air ratio in response to both said sensed pressures and temperatures.
Claim 11
Dependent Claim
23 words
A method as set forth in claim 8 wherein the pressure sensing step is accomplished by sensing pressures upstream of the combustion apparatus.
Claim 12
Dependent Claim
20 words
A method as set forth in claim 8 wherein said sensed pressures are the compressor discharge pressures of the engine.
Claim 13
Dependent Claim
18 words
A method as set forth in claim 8 wherein said sensed temperatures are those at the engine inlet.
Claim 14
Dependent Claim
16 words
A method as set forth in claim 8 wherein said combustion apparatus comprises an engine afterburner.
Claim 15
Dependent Claim
26 words
A method as set forth in claim 8 wherein said maintaining step includes the step of generating a pressure schedule in response to said sensed temperatures.
Claim 16
Dependent Claim
24 words
A method as set forth in claim 13 wherein said maintaining step includes the step of comparing said generated schedule with said sensed pressures.
Claim 17
Dependent Claim
96 words
An improved fuel control system for scheduling fuel flow to an afterburner in response to predetermined engine operating parameters wherein the improvement comprises: a. means for sensing pressures representative of those in the afterburner; b. means for sensing temperatures representative of those in the afterburner; c. means for generating in terms of one of the engine operating parameters a schedule indicative of the combustor rich stability limit; and d. means for maintaining operation of the engine within the rich stability limit by modifying the fuel flow schedule in response to both said sensed pressures and temperatures.
Claim 18
Dependent Claim
96 words
An improved fuel control system for scheduling fuel flow to an afterburner in response to predetermined engine operating parameters wherein the improvement comprises: a. means for sensing pressures representative of those in the afterburner; b. means for sensing temperatures representative of those in the afterburner; c. means for generating in terms of one of the engine operating parameters a schedule indicative of the combustor rich stability limit; and d. means for maintaining operation of the engine within the rich stability limit by modifying the fuel flow schedule in response to both said sensed pressures and temperatures.
Claim 19
Dependent Claim
17 words
The fuel control system of claim 15 wherein said pressure sensing means measures the compressor discharge pressures.
Claim 20
Dependent Claim
17 words
The fuel control system of claim 15 wherein said temperature sensing means measures the engine inlet temperature.
Claim 21
Dependent Claim
24 words
An improved fuel control system as set forth in claim 1 wherein said schedule generating means operates in response to said temperature sensing means.
Claim 22
Dependent Claim
25 words
An improved fuel control system as set forth in claim 1 wherein said schedule generating means generates a schedule in terms of compressor discharge pressures.
Claim 23
Dependent Claim
29 words
An improved fuel control system as set forth in claim 19 wherein said maintaining means includes means for comparing said schedule with the output from said pressure sensing means.
Claim 24
Dependent Claim
27 words
An improved method of stabilizing a fuel control system as set forth in claim 8 wherein said generating step is accomplished in response to said temperature sensed.
Claim 25
Dependent Claim
27 words
An improved method of stabilizing a fuel control system as set forth in claim 8 wherein said generating step results in a schedule of compressor discharge pressures.
Claim 26
Dependent Claim
37 words
An improved method of stabilizing a fuel control system as set forth in claim 22 wherein said maintaining step includes the step of comparing said schedule with said pressure representative of the air pressure in the combustor.
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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) | 1981-12-11 | 1982-06-12 | 1982-12-12 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-12-11 | 1986-06-12 | 1986-12-12 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-12-11 | 1990-06-12 | 1990-12-12 | $7700.00 | Window Closed / Lapsed |