US3842595A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Modular gas turbine engine
Assignee: General Electric Co
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Filing: 1972-12-26
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Granted: 1974-10-22
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Expires: 1992-12-26
Abstract
Abstract A modular gas turbine engine for an aircraft includes a cold module, a combustion liner assembly, a nozzle diaphragm assembly, and a gas generator turbine module, all of which may be readily removed and replaced in the field without the use of special tools. The invention herein described was made in the course of, or under a contract or subcontract thereunder (or grant), with the Department of the Army.
Inventors
- 👤 J Smith
- 👤 J Baxter
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 12:15
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/20; Y; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49229; Y10T29/49231; Y10T29/49234
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
345 words
A modular gas turbine engine comprises: a cold module which includes a casing open at one end to provide an inlet and extending rearwardly to form a combustor outer casing, a frame disposed within the cold module, a shaft journaled for rotation within the frame by bearings located entirely within the cold module, and a compressor which receives and pressurizes an inlet airflow; a combustion liner assembly for receiving the pressurized airflow from the compressor, togetheer with an inlet flow of fuel within the high pressure air and fuel mixture is ignited to produce a high energy gas stream; a nozzle diaphragm assembly for receiving and directing the high energy gas stream from the combustion chamber wherein the nozzle diaphragm includes a plurality of arcuate segments assembled on a circumferential support ring to form a flow annulus which may be attached to the engine frame by a first plurality of circumferentially spaced apart bolts which pass through and engage the support ring; an d a turbine module which receives the high energy gas stream from the nozzle diaphragm assembly and is drivably connected to the compressor through the shaft wherein the turbine module includes at least one rotor disc which is maintained in axially spaced engaged relation to the aft end of the shaft by a second plurality of circumferentially spaced apart bolts which pass through the entire turbine module thus facilitating ready access to the second plurality of bolts from the aft end thereof in order to permit intact removal and replacement of the turbine module from the aft end of the engine without removing a bearing or any portion thereof and wherein torque is transmitted from the turbine module to the shaft through an interconnecting toothed coupling, and wherein the turbine module includes a forward and an aft rotor disc maintained in axially spaced abuttin relation by a third plurality of circumferentially spaced apart elongated bolts extending therethrough in interspaced relation to the second plurality of bolts with torque transfer between the forward and aft rotor discs accomplished through an interconnecting tooth coupling.
Claim 2
Dependent Claim
345 words
A modular gas turbine engine comprises: a cold module which includes a casing open at one end to provide an inlet and extending rearwardly to form a combustor outer casing, a frame disposed within the cold module, a shaft journaled for rotation within the frame by bearings located entirely within the cold module, and a compressor which receives and pressurizes an inlet airflow; a combustion liner assembly for receiving the pressurized airflow from the compressor, togetheer with an inlet flow of fuel within the high pressure air and fuel mixture is ignited to produce a high energy gas stream; a nozzle diaphragm assembly for receiving and directing the high energy gas stream from the combustion chamber wherein the nozzle diaphragm includes a plurality of arcuate segments assembled on a circumferential support ring to form a flow annulus which may be attached to the engine frame by a first plurality of circumferentially spaced apart bolts which pass through and engage the support ring; an d a turbine module which receives the high energy gas stream from the nozzle diaphragm assembly and is drivably connected to the compressor through the shaft wherein the turbine module includes at least one rotor disc which is maintained in axially spaced engaged relation to the aft end of the shaft by a second plurality of circumferentially spaced apart bolts which pass through the entire turbine module thus facilitating ready access to the second plurality of bolts from the aft end thereof in order to permit intact removal and replacement of the turbine module from the aft end of the engine without removing a bearing or any portion thereof and wherein torque is transmitted from the turbine module to the shaft through an interconnecting toothed coupling, and wherein the turbine module includes a forward and an aft rotor disc maintained in axially spaced abuttin relation by a third plurality of circumferentially spaced apart elongated bolts extending therethrough in interspaced relation to the second plurality of bolts with torque transfer between the forward and aft rotor discs accomplished through an interconnecting tooth coupling.
Claim 3
Dependent Claim
22 words
The gas turbine engine of claim 1 wherein the second plurality of bolts is disposed outside the circumference of the toothed coupling.
Claim 4
Dependent Claim
49 words
The gas turbine engine of claim 2 wherein the turbine module includes a casing having a generally radially extending circumferential flange which may be attached to a second generally radially extending circumferential flange from the cold module casing by a fourth plurality of circumferentiaLly spaced apart bolts extending therethrough.
Claim 5
Dependent Claim
60 words
The gas turbine engine of claim 3 wherein there is further included a nozzle diaphragm intermediate the forward and aft rotor discs and in attachment to the turbine module casing such that the turbine module may be removed in its entirety from the aft end of the cold module by loosening and removing the second and fourth plurality of bolts.
Claim 6
Dependent Claim
158 words
The gas turbine engine of claim 3 wherein the support ring is an integral annulus and each arcuate segment of the nozzle diaphragm assembly includes an inner arcuate shroud segment from which extend radially outward a plurality off circumferentially spaced apart vanes into engagement with an outer arcuate shroud segment and wherein each inner arcuate shroud segment includes an integral arcuate flange segment extending radially inward therefrom into abutting engagement with a circumferential flange extending radially outward from the support ring together with a fifth plurality of circumferentially spaced apart bolts extending through the arcuate flange segments and the support ring circumferential flange so as to maintain their abutting relation and further including a circumferential seal ring engaged by the fifth plurality of bolts to reduce the flow leakage between the arcuate nozzle segments wherein the nozzle diaphragm may be removed and replaced intact from the aft end of the engine after the turbine module has been removed.
Claim 7
Dependent Claim
33 words
The gas turbine engine of claim 5 wherein the support ring includes a forward circumferential integral flange for engagement with the cold module frame and through which the first plurality of bolts extend.
Claim 8
Dependent Claim
120 words
The gas turbine engine of claim 3 wherein there is included a flow seal between the nozzle diaphragm assembly and turbine module having a stator member attached to the circumferential support ring and engaged by the teeth of a rotating member attached to the turbine module such that the rotating member may be readily withdrawn with the turbine module in an axially aft direction and wherein there is also included a flow seal between the shaft and cold module frame having a second stator member attached to the frame and engaged by the teeth of a second rotating member attached to the shaft such that the rotating member may be readily withdrawn with the turbine in an axially aft direction.
Claim 9
Dependent Claim
35 words
The gas turbine engine of claim 1 wherein the combustion liner assembly includes a circumferential lip extending radially inward from the aft edge thereof for axially locating the combustion liner assembly relative to the frame.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-10-21 | 1978-04-22 | 1978-10-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-10-21 | 1982-04-22 | 1982-10-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-10-21 | 1986-04-22 | 1986-10-22 | $7700.00 | Window Closed / Lapsed |