Patent US2125232A successfully refreshed from Google Patents.
Patent US4668162A successfully refreshed from Google Patents.
US4668162A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Changeable cooling control system for a turbine shroud and rotor
Assignee: Solar Turbines Inc
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Filing: 1985-09-16
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Granted: 1987-05-26
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Expires: 2005-09-16
Abstract
Abstract Cooling air delivery systems for gas turbine engines are used to increase component life and increase efficiencies. To change the flow rate of cooling air in past engines, major disassembly of engine components was required resulting in the loss of the engine's service and excessive costs. With the changeable cooling air delivery system of the present invention, major engine disassembly is eliminated. An elongate member extends into a fluid control passage to establish a preselected flow area which can be changed. The time and expense required to change the cooling flow rate is drastically reduced because the elongate members are accessible external of the engine. The elongate member is removed from the engine and replaced by different elongate member having a different outer diameter of the stem or sleeve. The different diameter results in a new clearance or preselected flow area for cooling air to pass therethrough.
Inventors
- 👤 Philip J. Cederwall
- 👤 David M. Evans
- 👤 Boris Glezer
- 👤 John J. Hensley
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 02:45
CPC Classifications
F; F01; F01D; F01D21/00; F01D21/003; B; B23; B23B; B23B51/00; F02; F02C; F02C7/00; F02C7/12; F02C7/16; F02C7/18; Y; Y10; Y10S; Y10S415/00; Y10S415/912
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
198 words
A cooling air delivery system for cooling components of a gas turbine engine having a compressor section and a compressor discharge plenum fluidly connecting the air delivery system to the compressor section comprising: a fluid flow path interconnecting the compressor discharge plenum with the engine components to be cooled, said fluid flow path including a fluid flow control passage; and an elongate member extending into said passage and having an outer diameter selected to establish a flow rate of cooling air through the remainder of the passage in accordance with predetermined operating parameters of the engine, said member having a portion thereof accessible externally of the engine, wherein said fluid flow path includes an annular cooling passages, a plurality of passages communicating the annular cooling passage with the engine components to be cooled, said control passage communicating cooling air from the compressor discharge plenum to the annular cooling passage, wherein said elongate member includes a stem and a sleeve having an outer diameter and being removably attached to the stem, wherein said fluid control passage has a preselected fixed diameter and said outer diameter of the sleeve being smaller than said preselected diameter establishing a preselected flow area.
Claim 2
Dependent Claim
198 words
A cooling air delivery system for cooling components of a gas turbine engine having a compressor section and a compressor discharge plenum fluidly connecting the air delivery system to the compressor section comprising: a fluid flow path interconnecting the compressor discharge plenum with the engine components to be cooled, said fluid flow path including a fluid flow control passage; and an elongate member extending into said passage and having an outer diameter selected to establish a flow rate of cooling air through the remainder of the passage in accordance with predetermined operating parameters of the engine, said member having a portion thereof accessible externally of the engine, wherein said fluid flow path includes an annular cooling passages, a plurality of passages communicating the annular cooling passage with the engine components to be cooled, said control passage communicating cooling air from the compressor discharge plenum to the annular cooling passage, wherein said elongate member includes a stem and a sleeve having an outer diameter and being removably attached to the stem, wherein said fluid control passage has a preselected fixed diameter and said outer diameter of the sleeve being smaller than said preselected diameter establishing a preselected flow area.
Claim 3
Dependent Claim
33 words
The cooling air delivery system of claim 1 wherein said fluid flow path includes a plurality of fluid flow control passages and said cooling air delivery system includes a plurality of elongate members.
Claim 4
Dependent Claim
37 words
The cooling air delivery system of claim 2 wherein said fluid control passage has a preselected fixed diameter and said outer diameter of the elongate member being smaller than said preselected diameter establishing a preselected flow area.
Claim 5
Dependent Claim
41 words
The cooling air delivery system of claim 1 wherein said fluid flow path further includes a plurality of orificed passages interconnecting the first annular portion with the annular cooling passage forming a combined total flow area to cool the engine components.
Claim 6
Dependent Claim
202 words
A gas turbine engine including a cooling air delivery system for cooling a nozzle vane, a turbine rotor, a compressor section and a compressor discharge plenum fluidly connecting the air delivery system to the compressor section comprising: a fluid flow path interconnecting the compressor discharge plenum with the nozzle vane to be cooled, said fluid flow path including a fluid flow control passage; and an elongate member extending into said passage and having an outer diameter selected to establish a flow rate of cooling air through the reminder of the passage in accordance with predetermined operating parameters of the engine, said member having a portion thereof accessible external of the engine wherein said fluid flow path includes an annular cooling passage, a plurality of passages communicating the annular cooling passage with the engine components to be cooled, said control passage communicating cooling air from the compressor discharge plenum to the annular cooling passage, wherein said elongate member includes a stem a sleeve having an outer diameter and being removably attached to the stem, wherein said fluid control passage has a preselected fixed diameter and said outer diameter of the elongate member bieng smaller then said preselected diameter establishing a preselected flow area.
Claim 7
Dependent Claim
202 words
A gas turbine engine including a cooling air delivery system for cooling a nozzle vane, a turbine rotor, a compressor section and a compressor discharge plenum fluidly connecting the air delivery system to the compressor section comprising: a fluid flow path interconnecting the compressor discharge plenum with the nozzle vane to be cooled, said fluid flow path including a fluid flow control passage; and an elongate member extending into said passage and having an outer diameter selected to establish a flow rate of cooling air through the reminder of the passage in accordance with predetermined operating parameters of the engine, said member having a portion thereof accessible external of the engine wherein said fluid flow path includes an annular cooling passage, a plurality of passages communicating the annular cooling passage with the engine components to be cooled, said control passage communicating cooling air from the compressor discharge plenum to the annular cooling passage, wherein said elongate member includes a stem a sleeve having an outer diameter and being removably attached to the stem, wherein said fluid control passage has a preselected fixed diameter and said outer diameter of the elongate member bieng smaller then said preselected diameter establishing a preselected flow area.
Claim 8
Dependent Claim
32 words
The gas turbine engine of claim 5 wherein said fluid flow path includes a plurality of fluid flow control passages and said cooling air delivery system includes a plurality of elongate members.
Claim 9
Dependent Claim
18 words
The gas turbine engine of claim 5 wherein said elongate member includes a stem having in outer diameter.
Claim 10
Dependent Claim
44 words
The gas turbine engine of claim 5 wherein said fluid flow path further includes a plurality of orificed passages interconnecting the first annular portion with the annular cooling passage forming a combined total flow area to cool the nozzle vane and the turbine rotor.
Claim 11
Independent Claim
105 words
A method of optimizating a flow rate of a cooling air delivery system for cooling components of a gas turbine engine, said cooling air delivery system having a fluid flow control passage and an elongate member extending into said passage to establish a flow rate of cooling air through the remainder of the passage, the improvement comprising the steps of: removing the elongate member from said flow control passage; measuring an outer diameter of the elongate member; determining the desire flow rate required; and installing into said flow control passage an elongate member having one of a smaller outer diameter and a larger outer diameter.
Claim 12
Independent Claim
105 words
A method of optimizating a flow rate of a cooling air delivery system for cooling components of a gas turbine engine, said cooling air delivery system having a fluid flow control passage and an elongate member extending into said passage to establish a flow rate of cooling air through the remainder of the passage, the improvement comprising the steps of: removing the elongate member from said flow control passage; measuring an outer diameter of the elongate member; determining the desire flow rate required; and installing into said flow control passage an elongate member having one of a smaller outer diameter and a larger outer diameter.
Claim 13
Independent Claim
134 words
A method of optimizating a flow rate of a cooling air delivery system for cooling components of a gas turbine engine, said cooling air delivery system having a fluid flow control passage and an elongate member having a stem and a sleeve being removably attached to the stem, said elongate member and said sleeve extending into said passage to establish a flow rate of cooling air through the remainder of the Passage, the improvement comprising the steps of: removing said elongate member from said fluid flow control passage; determining the desired flow rate required; removing said sleeve from said stem; attaching to the stem a new sleeve having one of a smaller outer diameter and a larger outer diameter; and reinstalling into said fluid flow control passage the elongate member having the new sleeve.
Claim 14
Independent Claim
134 words
A method of optimizating a flow rate of a cooling air delivery system for cooling components of a gas turbine engine, said cooling air delivery system having a fluid flow control passage and an elongate member having a stem and a sleeve being removably attached to the stem, said elongate member and said sleeve extending into said passage to establish a flow rate of cooling air through the remainder of the Passage, the improvement comprising the steps of: removing said elongate member from said fluid flow control passage; determining the desired flow rate required; removing said sleeve from said stem; attaching to the stem a new sleeve having one of a smaller outer diameter and a larger outer diameter; and reinstalling into said fluid flow control passage the elongate member having the new sleeve.
References Cited (Backward Citations)
US2640319A
Cited
US2639579A
Cited
GB737245A
Cited
US3199294A
Cited
US3211423A
Cited
US3295823A
Cited
US3452542A
Cited
US4173120A
Cited
US4428713A
Cited
US4416111A
Cited
US4478551A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1990-05-25 | 1990-11-24 | 1991-05-26 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1994-05-25 | 1994-11-24 | 1995-05-26 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1998-05-25 | 1998-11-24 | 1999-05-26 | $7700.00 | Window Closed / Lapsed |