US4815928A
Expired / Lapsed
US
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Blade cooling
Assignee: General Electric Co
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Filing: 1985-05-06
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Granted: 1989-03-28
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Expires: 2005-05-06
Abstract
Abstract In one form of the present invention, turbine cooling air is modulated as a function of engine speed, altitude, and blade temperature.
Inventors
- 👤 Frederick J. Pineo
- 👤 Jose T. Alvarez
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 09:09
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/02; F01D5/08; F01D5/081; F02; F02C; F02C7/00; F02C7/12; F02C7/16; F02C7/18; F02C9/00; F02C9/16; F02C9/18; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
30 words
In the cooling airflow for turbine blades in a gas turbine aircraft engine, the improvement comprising: maintaining and terminating cooling airflow based upon aircraft altitude, engine speed, and blade temperature.
Claim 2
Dependent Claim
30 words
In the cooling airflow for turbine blades in a gas turbine aircraft engine, the improvement comprising: maintaining and terminating cooling airflow based upon aircraft altitude, engine speed, and blade temperature.
Claim 3
Independent Claim
120 words
A method of controlling a cooling airflow for turbine blades in an aircraft, comprising the following steps: (a) establishing a schedule of engine threshold speeds comprising: (i) a first speed when the aircraft altitude is above a first predetermined altitude (42); (ii) a second speed when the aircraft is below a second predetermined altitude (45); (iii) a series of linearly interpolated speeds when the aircraft is between the first and second altitudes; (b) maintaining cooling air when the actual speed exceeds the threshold speed and, if not, then (c) maintaining cooling air when the blade temperature exceeds a predetermined limit and, if not, then (d) terminating cooling air when the blade temperature falls below the limit by a predetermined amount.
Claim 4
Independent Claim
120 words
A method of controlling a cooling airflow for turbine blades in an aircraft, comprising the following steps: (a) establishing a schedule of engine threshold speeds comprising: (i) a first speed when the aircraft altitude is above a first predetermined altitude (42); (ii) a second speed when the aircraft is below a second predetermined altitude (45); (iii) a series of linearly interpolated speeds when the aircraft is between the first and second altitudes; (b) maintaining cooling air when the actual speed exceeds the threshold speed and, if not, then (c) maintaining cooling air when the blade temperature exceeds a predetermined limit and, if not, then (d) terminating cooling air when the blade temperature falls below the limit by a predetermined amount.
Claim 5
Independent Claim
138 words
A method of controlling cooling air to turbine blades in a gas turbine aircraft engine, comprising the following steps: (a) defining a first data point (42) comprising a first predetermined engine speed and a first predetermined altitude; (b) defining a second data point (45) comprising a second predetermined engine speed and a second predetermined altitude; (c) linearly interpolating between the first and second data points; and (d) maintaining cooling airflow unless one of the following conditions occur, whereupon cooling airflow is terminated: (i) engine speed is below the first predetermined engine speed and the aircraft is above the first predetermined altitude; (ii) engine speed is below the second predetermined engine speed and the aircraft is below the second predetermined altitude; (iii) engine speed falls below the interpolation when the aircraft is between the first and second predetermined altitudes.
Claim 6
Independent Claim
138 words
A method of controlling cooling air to turbine blades in a gas turbine aircraft engine, comprising the following steps: (a) defining a first data point (42) comprising a first predetermined engine speed and a first predetermined altitude; (b) defining a second data point (45) comprising a second predetermined engine speed and a second predetermined altitude; (c) linearly interpolating between the first and second data points; and (d) maintaining cooling airflow unless one of the following conditions occur, whereupon cooling airflow is terminated: (i) engine speed is below the first predetermined engine speed and the aircraft is above the first predetermined altitude; (ii) engine speed is below the second predetermined engine speed and the aircraft is below the second predetermined altitude; (iii) engine speed falls below the interpolation when the aircraft is between the first and second predetermined altitudes.
Claim 7
Dependent Claim
48 words
A method according to claim 3, and further comprising: maintaining cooling airflow, irrespective of the three conditions of step (d)(i), (ii) and (iii), when the blade temperature exceeds a first temperature; and terminating cooling airflow when the blade temperature falls below the first temperature by a predetermined amount.
Claim 8
Dependent Claim
206 words
In an aircraft having a gas turbine engine containing a valve which controls cooling airflow to turbine blades, the improvement comprising: (a) speed sensor means for producing an actual speed signal indicative of the rotational speed of a predetermined engine component; (b) pressure sensor means for producing a pressure signal indicative of the altitude of the aircraft; (c) temperature sensor means for producing a blade temperature signal indicative of the temperature of the turbine blades; (d) scheduling means coupled to both sensor means of (a) and (b) for producing a threshold speed signal as a function of the actual speed signal and the pressure signal; (e) servo means for (i) comparing the threshold speed signal with the actual speed signal and opening the valve when the actual speed exceeds the threshold speed; (ii) comparing the blade temperature signal with a first temperature limit and opening the valve when the blade temperature exceeds the first temperature limit; (iii) comparing the blade temperature signal with a second temperature limit and in response (A) closing the valve when the blade temperature falls below the second limit and (B) maintaining the valve in its present state, i.e., either open or closed, when the blade temperature is above the second limit.
Claim 9
Dependent Claim
206 words
In an aircraft having a gas turbine engine containing a valve which controls cooling airflow to turbine blades, the improvement comprising: (a) speed sensor means for producing an actual speed signal indicative of the rotational speed of a predetermined engine component; (b) pressure sensor means for producing a pressure signal indicative of the altitude of the aircraft; (c) temperature sensor means for producing a blade temperature signal indicative of the temperature of the turbine blades; (d) scheduling means coupled to both sensor means of (a) and (b) for producing a threshold speed signal as a function of the actual speed signal and the pressure signal; (e) servo means for (i) comparing the threshold speed signal with the actual speed signal and opening the valve when the actual speed exceeds the threshold speed; (ii) comparing the blade temperature signal with a first temperature limit and opening the valve when the blade temperature exceeds the first temperature limit; (iii) comparing the blade temperature signal with a second temperature limit and in response (A) closing the valve when the blade temperature falls below the second limit and (B) maintaining the valve in its present state, i.e., either open or closed, when the blade temperature is above the second limit.
Claim 10
Independent Claim
81 words
An apparatus for controlling cooling airflow for turbine blades in an aircraft gas turbine engine, comprising: a means for producing a signal related to the rotational speed for a predetermined engine component; a means for producing a signal related to the altitude of the aircraft; a means for producing a signal related to the temperature of the turbine blades; and a means connected to the speed, altitude, and temperature signal producing means for modulating the cooling airflow for the turbine blades.
Claim 11
Independent Claim
81 words
An apparatus for controlling cooling airflow for turbine blades in an aircraft gas turbine engine, comprising: a means for producing a signal related to the rotational speed for a predetermined engine component; a means for producing a signal related to the altitude of the aircraft; a means for producing a signal related to the temperature of the turbine blades; and a means connected to the speed, altitude, and temperature signal producing means for modulating the cooling airflow for the turbine blades.
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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) | 1992-03-27 | 1992-09-26 | 1993-03-28 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-03-27 | 1996-09-26 | 1997-03-28 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-03-27 | 2000-09-26 | 2001-03-28 | $7700.00 | Window Closed / Lapsed |