US3575522A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbine cooling
Assignee: Motors Liquidation Co
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Filing: 1968-08-30
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Granted: 1971-04-20
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Expires: 1988-08-30
Abstract
Abstract An arrangement for cooling the rim of the first to second stage spacer of a multistage turbine of a gas turbine engine. Cooling air supplied to the forward face of the first stage wheel flows through blade slots below the blade roots and is discharged from the turbine wheel over the outer surface of the adjacent spacer through the clearance gap between it and the inner shroud of the second stage nozzle. Some of the spaces under the blade bases are closed by inserted air seals to regulate the quantity of cooling air and spacer temperature drop desired.
Inventors
- 👤 Samuel Melenchuk
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 16:51
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/02; F01D5/08; F01D5/081; F01D5/084; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
205 words
A turbine comprising, in combination, a stator including a first stage nozzle and a second stage nozzle; a rotor including a first stage wheel, a second stage wheel, and a spacer mounted between and rotating with the said wheels, the wheels and spacer having abutting rims and the wheels having blades mounted on and extending from the rims; the outer surface of the spacer rim being slightly spaced from the second stage nozzle to define a radial gap between the spacer rim and nozzle; means in the gap providing a labyrinth seal to minimize bypassing of the second stage nozzle by motive fluid; and means for conducting cooling air to the forward face of the first stage wheel; the first stage rim defining passages through the rim for flow of cooling air from the forward to the rear face of the rim terminating in alignment with the said radial gap, the passages discharging cooling air jets axially of the rotor directed into the said radial gap to deliver the cooling air into the labyrinth seal so as to provide a film of cooling air over the outer surface of the spacer rim flowing from the forward edge to the rear edge of the spacer rim.
Claim 2
Dependent Claim
205 words
A turbine comprising, in combination, a stator including a first stage nozzle and a second stage nozzle; a rotor including a first stage wheel, a second stage wheel, and a spacer mounted between and rotating with the said wheels, the wheels and spacer having abutting rims and the wheels having blades mounted on and extending from the rims; the outer surface of the spacer rim being slightly spaced from the second stage nozzle to define a radial gap between the spacer rim and nozzle; means in the gap providing a labyrinth seal to minimize bypassing of the second stage nozzle by motive fluid; and means for conducting cooling air to the forward face of the first stage wheel; the first stage rim defining passages through the rim for flow of cooling air from the forward to the rear face of the rim terminating in alignment with the said radial gap, the passages discharging cooling air jets axially of the rotor directed into the said radial gap to deliver the cooling air into the labyrinth seal so as to provide a film of cooling air over the outer surface of the spacer rim flowing from the forward edge to the rear edge of the spacer rim.
Claim 3
Dependent Claim
24 words
A turbine as recited in claim 1 in which the rim defines blade mounting slots and the slots define the said cooling air passages.
Claim 4
Dependent Claim
21 words
A turbine as recited in claim 2 including air seals blocking some but not all of the said cooling air passages.
Claim 5
Dependent Claim
121 words
A turbine as recited in claim 1, the first stage wheel rim having dovetail slots extending across the rim and the blades having dovetail roots lodged in the slots, the blade roots having clearance from the bottoms of the slots to define cooling air passages extending axially of the rotor through the rim, air seals disposed in some of the blade slots closing the said passages, each air seal having a dovetail interlock with the walls of the blade slot to retain it radially of the rotor and being interlocked with the blade root to retain the air seal axially of the rotor, and means cooperating with the wheel and blade roots retaining the first stage blades axially of the rotor.
Claim 6
Dependent Claim
128 words
A turbine rotor comprising, in combination, a wheel having a rim, a row of blades mounted on the rim, the rim having dovetail slots extending across the rim and the blades having dovetail roots lodged in the slots, the blade roots having clearance from the bottoms of the slots to define cooling air passages extending axially of the rotor through the rim, air seals disposed in some of the blade slots closing the said passages, each air seal having a dovetail interlock with the walls of the blade slot to retain it radially of the rotor and being interlocked with the blade root to retain the air seal axially of the rotor, and means cooperating with the wheel and blade roots retaining the blades axially of the rotor.
Claim 7
Dependent Claim
128 words
A turbine rotor comprising, in combination, a wheel having a rim, a row of blades mounted on the rim, the rim having dovetail slots extending across the rim and the blades having dovetail roots lodged in the slots, the blade roots having clearance from the bottoms of the slots to define cooling air passages extending axially of the rotor through the rim, air seals disposed in some of the blade slots closing the said passages, each air seal having a dovetail interlock with the walls of the blade slot to retain it radially of the rotor and being interlocked with the blade root to retain the air seal axially of the rotor, and means cooperating with the wheel and blade roots retaining the blades axially of the rotor.
Claim 8
Dependent Claim
39 words
A rotor as recited in claim 5 including also an interstage spacer disposed and of and adjacent to the wheel rim and having an outer surface located to be bathed by air flowing from the said cooling air passages.
References Cited (Backward Citations)
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US2807434A
Cited
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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) | 1974-04-19 | 1974-10-19 | 1975-04-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-04-19 | 1978-10-19 | 1979-04-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-04-19 | 1982-10-19 | 1983-04-20 | $7700.00 | Window Closed / Lapsed |