Patent US4214756A successfully refreshed from Google Patents.
Patent US3751909A successfully refreshed from Google Patents.
US3751909A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbojet aero engines having means for engine component cooling and compressor control
Assignee: MTU Aero Engines AG
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Filing: 1971-08-26
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Granted: 1973-08-14
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Expires: 1991-08-26
Abstract
Abstract This invention relates to gas turbine engines, and, more particularly, to multishaft turbojet aero engines having a plurality of compressors and turbines, in which air is bled from one or several compressors in the engine for cooling engine components and for providing a seal between the rotary and stationary assemblies of the several rotor systems, and in which means are additionally provided for compressor control.
Inventors
- 👤 G Kohler
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 15:34
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/12; F02C7/16; F02C7/18; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/148; F04; F04D; F04D29/00; F04D29/26; F04D29/32; F04D29/321; F04D29/324; F04D29/66; F04D29/68; F04D29/681; F04D29/684; F04D27/00; F04D27/02; F04D27/0207; F04D27/0238; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10S; Y10S415/00; Y10S415/914
Claims Analysis
Total Claims: 20
Claim 1
Independent Claim
214 words
A multi-shaft gas turbine engine comprising: low pressure compressor means, low pressure turbine means, high pressure compressor means, high pressure turbine means, said high pressure compressor means being arranged in a casing means downstream of said low pressure compressor means for accepting discharge flow from said low pressure compressor means, port means opening into said casing means at a position intermediate said low pressure compressor means and said high pressure compressor means, first line means communicating said port means with cooling and sealing spaces of said engine, second line means communicating said port means with discharge flow from said high pressure compressor means, and control valve means for closing said second line means during a first range of engine operating conditions such that said port means and said first line means supply portions of the discharge flow from said low pressure compressor means as cooling and sealing air to said cooling and sealing spaces and for opening said second line means during a second range of engine operating conditions such that said second line means supplies portions of the discharge flow from said high pressure compressor means to said port means to produce aerodynamic swirl of the air supplied to the high pressure compressor means which prevents surging of said high pressure compressor means.
Claim 2
Dependent Claim
214 words
A multi-shaft gas turbine engine comprising: low pressure compressor means, low pressure turbine means, high pressure compressor means, high pressure turbine means, said high pressure compressor means being arranged in a casing means downstream of said low pressure compressor means for accepting discharge flow from said low pressure compressor means, port means opening into said casing means at a position intermediate said low pressure compressor means and said high pressure compressor means, first line means communicating said port means with cooling and sealing spaces of said engine, second line means communicating said port means with discharge flow from said high pressure compressor means, and control valve means for closing said second line means during a first range of engine operating conditions such that said port means and said first line means supply portions of the discharge flow from said low pressure compressor means as cooling and sealing air to said cooling and sealing spaces and for opening said second line means during a second range of engine operating conditions such that said second line means supplies portions of the discharge flow from said high pressure compressor means to said port means to produce aerodynamic swirl of the air supplied to the high pressure compressor means which prevents surging of said high pressure compressor means.
Claim 3
Dependent Claim
68 words
A gas turbine engine according to claim 1, wherein said first range corresponds to normal engine operation with said low pressure compressor means supplying sufficient discharge flow to efficiently supply said high pressure compressor means, and wherein said second range corresponds to engine starting conditions with said low pressure compressor means supplying a smaller discharge flow to said high pressure compressor means than during said normal engine operation.
Claim 4
Dependent Claim
101 words
A gas turbine engine according to claim 2, wherein at least one stationary support guide vane is positioned in said casing means intermediate said low pressure compressor means and said high pressure compressor means for guiding the discharge flow from said low pressure compressor means into rotatable blades of said high pressure compressor means, wherein said at least one guide vane contains a hollow space therein, wherein said port means extend from said hollow space to an exterior surface of said at least one guide vane, and wherein both of said first and second line means communicate with said hollow space.
Claim 5
Dependent Claim
56 words
A gas turbine engine according to claim 2, wherein said first and second line means are connected with one another such that said second line means supplies portions of the discharge flow from said high pressure compressor means as cooling and sealing air to said cooling and sealing spaces when said second line means is open.
Claim 6
Dependent Claim
101 words
A gas turbine engine according to claim 4, wherein at least one stationary support guide vane is positioned in said casing means intermediate said low pressure compressor means and said high pressure compressor means for guiding the discharge flow from said low pressure compressor means into rotatable blades of said high pressure compressor means, wherein said at least one guide vane contains a hollow space therein, wherein said port means extend from said hollow space to an exterior surface of said at least one guide vane, and wherein both of said first and second line means communicate with said hollow space.
Claim 7
Dependent Claim
90 words
A gas turbine engine according to claim 2, wherein a combustion chamber is arranged in said casing means downstream of said high pressure compressor means for accepting portions of the discharge flow from said high pressure compressor means, and wherein said second line means includes a by-pass line having one end opening into the discharge flow of the high pressure compressor means at a position upstream of said combustion chamber and the other end opening into at least one hollow turBine support vane means arranged downstream of said combustion chamber.
Claim 8
Dependent Claim
86 words
A gas turbine engine according to claim 6, wherein the high and low pressure turbine means are serially arranged downstream of said combustion chamber, wherein said at least one hollow turbine support vane means is arranged downstream of the low pressure turbine means, and wherein said second line means further includes a hollow turbine exhaust cone attached to said at least one hollow turbine support vane means and a hollow rotor shaft which drivingly connects said low pressure compressor means with said low pressure turbine means.
Claim 9
Dependent Claim
19 words
A gas turbine engine according to claim 7, wherein said control valve means is arranged in said by-pass line.
Claim 10
Dependent Claim
31 words
A gas turbine engine according to claim 8, wherein said first line means includes portions of said hollow rotor shaft, which last-mentioned portions also form part of said second line means.
Claim 11
Dependent Claim
101 words
A gas turbine engine according to claim 7, wherein at least one stationary support guide vane is positioned in said casing means intermediate said low pressure compressor means and said high pressure compressor means for guiding the discharge flow from said low pressure compressor means into rotatable blades of said high pressure compressor means, wherein said at least one guide vane contains a hollow space therein, wherein said port means extend from said hollow space to an exterior surface of said at least one guide vane, and wherein both of said first and second line means communicate with said hollow space.
Claim 12
Dependent Claim
56 words
A gas turbine engine according to claim 10, wherein said first and second line means are connected with one another such that said second line means supplies portions of the discharge flow from said high pressure compressor means as cooling and sealing air to said cooling and sealing spaces when said second line means is open.
Claim 13
Dependent Claim
31 words
A gas turbine engine according to claim 11, wherein said first line means includes portions of said hollow rotor shaft, which last-mentioned portions also form part of said second line means.
Claim 14
Dependent Claim
27 words
A gas turbine engine according to claim 3, wherein said port means are constructed as slots arranged adjacent trailing edges of said at least one guide vane.
Claim 15
Dependent Claim
70 words
A gas turbine engine according to claim 13, wherein said slots are configured to reduce the magnitude of the resultant velocity of air supplied to blades of said high pressure compressor means as well as to reorient said resultant velocity so as to be parallel to the chord of respective ones of said blades when high pressure compressor discharge flow is supplied to said slots by said second line means.
Claim 16
Dependent Claim
27 words
A gas turbine engine according to claim 12, wherein said port means are constructed as slots arranged adjacent trailing edges of said at least one guide vane.
Claim 17
Dependent Claim
70 words
A gas turbine engine according to claim 15, wherein said slots are configured to reduce the magnitude of the resultant velocity of air supplied to blades of said high pressure compressor means as well as to reorient said resultant velocity so as to be parallel to the chord of respective ones of said blades when high pressure compressor discharge flow is supplied to said slots by said second line means.
Claim 18
Dependent Claim
24 words
A gas turbine engine according to claim 2, wherein said port means are constructed as slots arranged in wall portions of said casing means.
Claim 19
Dependent Claim
70 words
A gas turbine engine according to claim 17, wherein said slots are configured to reduce the magnitude of the resultant velocity of air supplied to blades of said high pressure compressor means as well as to reorient said resultant velocity so as to be parallel to the chord of respective ones of said blades when high pressure compressor discharge flow is supplied to said slots by said second line means.
Claim 20
Dependent Claim
25 words
A gas turbine engine according to claim 2, wherein said sealing and cooling spaces include spaces in turbine blades of said low pressure turbine means.
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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) | 1976-08-13 | 1977-02-12 | 1977-08-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-08-13 | 1981-02-12 | 1981-08-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-08-13 | 1985-02-12 | 1985-08-14 | $7700.00 | Window Closed / Lapsed |