US3989410A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Labyrinth seal system
Assignee: General Electric Co
•
Filing: 1974-11-27
•
Granted: 1976-11-02
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Expires: 1994-11-27
Abstract
Abstract Undesired leakage from a system of labyrinth seals used to retain turbine cooling air is reduced by providing passageways which direct all parasitic leakage to a point between the teeth of one of the seals in the system.
Inventors
- 👤 Bartolomeo Joseph Ferrari
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 05:18
CPC Classifications
F; F01; F01D; F01D3/00; F01D11/00; F01D11/02; F01D5/00; F01D5/02; F01D5/08; F01D5/081
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
180 words
An improved gas turbine engine comprising a compressor, combustor, and gas turbine in serial flow relation, a rotor drivably connected to the gas turbine for driving the compressor, a first annular chamber for retaining cooling air, and a gas accelerator providing accelerated cooling air to the first chamber having an input in flow communciation with the compressor, and an output in flow communication with the first chamber, wherein the improvement comprises: a system of labyrinth seals for sealing the first chamber against leakage to and from adjacent areas of differing pressure, each seal having a toothed member in rotating engagement with a fixed runner; flow passage means for causing the leakages of all the seals to flow to a point between the teeth of a first one of the seals wherein the flow passage means includes a plurality of tubes circumferentially spaced about the input to the accelerator, each tube having an inlet disposed to receive parasitic leakage from the remaining seals and an outlet in flow communication with at least one aperture in the runner of the first seal.
Claim 2
Dependent Claim
180 words
An improved gas turbine engine comprising a compressor, combustor, and gas turbine in serial flow relation, a rotor drivably connected to the gas turbine for driving the compressor, a first annular chamber for retaining cooling air, and a gas accelerator providing accelerated cooling air to the first chamber having an input in flow communciation with the compressor, and an output in flow communication with the first chamber, wherein the improvement comprises: a system of labyrinth seals for sealing the first chamber against leakage to and from adjacent areas of differing pressure, each seal having a toothed member in rotating engagement with a fixed runner; flow passage means for causing the leakages of all the seals to flow to a point between the teeth of a first one of the seals wherein the flow passage means includes a plurality of tubes circumferentially spaced about the input to the accelerator, each tube having an inlet disposed to receive parasitic leakage from the remaining seals and an outlet in flow communication with at least one aperture in the runner of the first seal.
Claim 3
Dependent Claim
64 words
The gas turbine engine of claim 1 further comprising: a second annular chamber upstream and adjacent the first chamber; a compressor discharge passage in flow communication with the compressor and upstream and adjacent the second chamber, and a third annular chamber in flow communication with the combustor and downstream and adjacent the first chamber; an annular flow passage adjacent the accelerator and first chamber.
Claim 4
Dependent Claim
46 words
The gas turbine engine of claim 2 wherein: the first labyrinth seal separates the first chamber and the third chamber; a second labyrinth seal separates the second chamber and the compressor discharge passage, and a thrid labyrinth seal separates the first chamber and the second chamber.
Claim 5
Dependent Claim
29 words
A gas turbine engine as claimed in claim 3 wherein at least one wall of the second flow passage is formed by the runner of the first labyrinth seal.
Claim 6
Dependent Claim
17 words
The gas turbine engine of claim 1 wherein the first annular chamber is a balance piston chamber.
Claim 7
Dependent Claim
82 words
The gas turbine engine of claim 4 wherein each tube has its inlet in flow communication with the second annular chamber and its outlet in flow communication with the annular flow passage and further comprising a plurality of apertures circumferentially spaced around the runner of the first seal opposite a point between two of the teeth of the first seal such that parasitic leakage flows through the annular flow passage and thereafter between the first and second teeth of the first seal.
Claim 8
Dependent Claim
36 words
A gas turbine engine as claimed in claim 6 wherein the apertures in the seal runner of the first labryinth seal are located at a point between the two upstream teeth of the first labyrinth seal.
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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) | 1979-11-02 | 1980-05-03 | 1980-11-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-11-02 | 1984-05-03 | 1984-11-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-11-02 | 1988-05-03 | 1988-11-02 | $7700.00 | Window Closed / Lapsed |